SolidWorks Simulation 2010 Validation

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SUMMARY

The purpose of this report is to present the accuracy of results given by SolidWorks simulation 2010 using the Guide de validation des progiciels de calcul de structures (Structural Analysis Software Validation Guide) published by AFNOR (Association Française de NORmalisation, French Standardization Association). 100 validation examples (linear static analysis, vibration, dynamic response, thermal, nonlinear) from the guide are analyzed. Results given by SolidWorks Simulation generally fall within 1% of the ideal solution.

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BASED ON THE GUIDE DE VALIDATION DES PROGICIELS DE CALCULS DE STRUCTURES, by AFNOR

INTRODUCTION

The purpose of this report is to present the accuracy of results given by SolidWorks Simulation 2010 using the Guide de validation des progiciels de calcul de structures

(Structural Analysis Software Validation Guide). This guide was published by AFNOR (Association Française de NORmalisation, French Standardization Association) and written and compiled by the SFM (Société Française des Mécaniciens). It is a compilation of 143 validation examples for Finite Elements Analysis software. The validation examples belong to a wide range of domains: linear static analysis, vibration, dynamic response, thermal, nonlinear, fluid mechanics. Not all of them fit in the range of analysis capabilities of SolidWorks Simulation. That’s the case of the validation examples in fluid dynamics, for instance. Therefore, a set of 100 examples were selected. They are presented in this report using the evaluation form template provided in the guide. In addition to the form, screen captures of the model and results have been added when useful for a better understanding. However, information about each model’s geometry, material properties, loads and boundary conditions have not been copied into this report. To obtain all the above information, the reader should refer to the guide itself. While modeling each problem in SolidWorks Simulation, the intent has been to meticulously follow the modeling guidelines recommended for each example. When not possible, an equivalent approach was used. For instance, when it was not possible to perform a study with the recommended element type, and equivalent study was set up with another element type. As you will see in this report, results given by SolidWorks Simulation generally fall within 1% of the reference solution.

Julien Boissat SolidWorks Simulation Senior Technical Support Engineer

SolidWorks Simulation 2010 VALIDATION

no. 2

CONTENTS

I.

STRUCTURAL MECHANICS .............................. ..................................................... ............................................. ............................. ....... 9 1.

Linear static ...................................................... ............................................................................ ............................................. ............................... ........ 10 SLENDER BEAM WITH BOTH ENDS FIXED SSLL 01‐89 .............................................................................................................................10 ............................................................................................................................. 10 SLENDER BEAM ON THREE SIMPLE SUPPORTS SSLL 03‐89 .............................................................................................................................11 ............................................................................................................................. 11 BIMETALLIC STRIP FIXED ON BOTH ENDS CONNECTED WITH A RIGID BAR SSLL 05‐89 .............................................................................................................................12 ............................................................................................................................. 12 FIXED THIN ARC UNDER INPLANE BENDING SSLL 06‐89 .............................................................................................................................13 ............................................................................................................................. 13 FIXED THIN ARC UNDER OUT OF PLANE BENDING SSLL 07‐89 .............................................................................................................................14 ............................................................................................................................. 14 SIMPLY SUPPORTED THIN ARC UNDER INPLANE BENDING SSLL 08‐89 .............................................................................................................................15 ............................................................................................................................. 15 TWO BAR SYSTEM WITH THREE UNIVERSAL JOINTS SSLL 09‐89 .............................................................................................................................16 ............................................................................................................................. 16 FRAME WITH LATERAL CONNECTIONS SSLL 10‐89 .............................................................................................................................17 ............................................................................................................................. 17 FRAMEWORK OF ARTICULATED BASR UNDER CONCENTRATED LOAD SSLL 11‐89 .............................................................................................................................18 ............................................................................................................................. 18 PRE‐STRESSED BAR SSLL 13‐89 .............................................................................................................................19 ............................................................................................................................. 19 SIMPLY SUPPORTED PLANAR FRAME SSLL 14‐89 .............................................................................................................................20 ............................................................................................................................. 20 PLATE UNDER BENDING AND SHEAR IN ITS OWN PLANE SSLP 01‐89............................................................................................................................. 89.............................................................................................................................21 21 PERFORATED PLATE UNDER SIMPLE TRACTION SSLP 02‐89............................................................................................................................. 89.............................................................................................................................23 23 CANTILEVER RECTANGULAR PLATE SSLS 01‐89............................................................................................................................. 89 .............................................................................................................................24 24 SIMPLY SUPPORTED SQUARE PLATE SSLS 02‐89............................................................................................................................. 89 .............................................................................................................................25 25 CIRCULAR PLATE UNDER UNIFORM PRESSURE LOAD SSLS 03‐89............................................................................................................................. 89 .............................................................................................................................26 26

RECTANGULAR HOLLOW BEAM UNDER TORSION SSLS 05‐89............................................................................................................................. 89 .............................................................................................................................27 27


no. 3

CONTENTS

THIN CYLINDER UNDER UNIFORM RADIAL PRESSURE SSLS 06‐89.............................................................................................................................28 THIN CYLINDER UNDER UNIFORM AXIAL PRESSURE SSLS 07‐89.............................................................................................................................29 THIN CYLINDER UNDER HYDROSTATIC PRESSURE SSLS 08‐89.............................................................................................................................30 THIN CYLINDER UNDER ITS OWN WEIGHT SSLS 09‐89.............................................................................................................................31 TORE UNDER INTERNAL UNIFORM PRESSURE SSLS 10‐89.............................................................................................................................32 SPHERICAL CAP UNDER INTERNAL PRESSURE SSLS 14‐89.............................................................................................................................33 SPHERICAL CAP UNDER RADIAL FORCE SSLS 15‐89.............................................................................................................................34 SPHERICAL CAP UNDER MOMENT SSLS 16‐89.............................................................................................................................35 SPHERICAL CAP UNDER ITS OWN WEIGHT SSLS 17‐89.............................................................................................................................36 SPHERICAL CAP UNDER IMPOSED DISPLACEMENT SSLS 18‐89.............................................................................................................................37 CYLINDRICAL SHELL UNDER ITS OWN WEIGHT SSLS 19‐89.............................................................................................................................38 PINCHED CYLINDRICAL SHELL SSLS 20‐89.............................................................................................................................39 SPHERICAL SHELL WITH HOLE SSLS 21‐89.............................................................................................................................40 SPHERICAL CAP UNDER EXTERNAL UNIFORM PRESSURE SSLS 22‐89.............................................................................................................................41 CYLINDRICAL MEMBRANE UNDER BENDING SSLS 23‐89.............................................................................................................................42 SIMPLY SUPPORTED RECTANGULAR PLATE UNDER UNIFORM PRESSURE SSLS 24‐89.............................................................................................................................43

SIMPLY SUPPORTED RHOMB PLATE UNDER BENDING SSLS 25‐89.............................................................................................................................44 : PLATE UNDER NORMAL SHEAR SSLS 27‐89.............................................................................................................................45


no. 4

CONTENTS

FULL CYLINDER UNDER SIMPLE TRACTION SSLV 01‐89 ............................................................................................................................46 FULL SPHERE UNDER UNIFORM PRESSURE SSLV 02‐89 ............................................................................................................................47 THICK SPHERICAL TANK UNDER INTERNAL PRESSURE SSLV 03‐89 ............................................................................................................................48 THICK INFINITE PIPE UNDER INTERNAL PRESSURE SSLV 04‐89 ............................................................................................................................49 BEAM WITH ELLIPTIC CROSS SECTION UNDER TORSION SSLV 05‐89 ............................................................................................................................50 RECTANGULAR SECTION SHAPE BEAM UNDER TORSION SSLV 06‐89 ............................................................................................................................51 BLOCK STRETCHED UNDER ITS OWN WEIGHT SSLV 07‐89 ............................................................................................................................52 PRISMATIC BEAM UNDER PURE BENDING SSLV 08‐89 ............................................................................................................................53 THICK PLATE WITH ITS EDGES FIXED SSLV 09‐89 ............................................................................................................................54

2. Non linear static .................................................................................................... 56 RECTANGLE UNDER PURE BENDING (PLANE STRESS, PERFECT PLASTICITY) SSNP 11‐89............................................................................................................................56 CYLINDER UNDER PRESSURE (PLANE STRAIN, PERFECT ELASTOPLASTICITY) SSNP 13‐89............................................................................................................................57

3.

Linear dynamic ...................................................................................................... 59 THIN CYLINDER FIXED ON BOTH ENDS SDLA 01‐89............................................................................................................................59 SLENDER FOLDED BEAM, ONE END FIXED THE OTHER FREE SDLL 02‐89 ............................................................................................................................61 SLENDER BEAM ON TWO SIMPLE SUPPORTS UNDER AXIAL FORCE SDLL 05‐89 ............................................................................................................................62

PLANAR FRAME MADE OF I BEAMS SDLL 08‐89 ............................................................................................................................63 SLENDER BEAM WITH VARIABLE RECTANGULAR SECTION, ONE END FIXED THE OTHER FREE SDLL 09‐89 ............................................................................................................................64 SLENDER BEAM WITH VARIABLE RECTANGULAR SECTION, BOTH ENDS FIXED SDLL 10‐89 ............................................................................................................................65


no. 5

CONTENTS

THIN CIRCULAR RING COMPLETELY FREE SDLL 11‐89 ............................................................................................................................67 THIN CIRCULAR RING FIXED AT TWO POINTS SDLL 12‐89 ............................................................................................................................69 THIN CIRCULAR RING FIXED BY AN ELASTIC LEG SDLL 13‐89 ............................................................................................................................71 VIBRATION MODES OF AN ELBOWED PIPE SDLL 14‐89 ............................................................................................................................73 THIN FREE RING WITH A PUNCTUAL MASS SDLL 16‐89 ............................................................................................................................75 THIN SQUARE PLATE WITH 3 OR 4 FREE EDGES SDLS 01‐89 ............................................................................................................................77 THIN RHOMBOID PLATE FIXED ON ONE EDGE SDLS 02‐89 ............................................................................................................................79 THIN RECTANGULAR PLATE SIMPLY SUPPORTED ON EDGES SDLS 03‐89 ............................................................................................................................80 THIN RING SHAPED PLATE FIXED ON INNER EDGE SDLS 04‐89 ............................................................................................................................82 COMPRESSOR BLADE: THIN SHELL FIXED‐FREE SDLS 05‐89 ............................................................................................................................84 THIN WINGED CIRCULAR PLATE SDLS 06‐89 ............................................................................................................................86 THIN SPHERE COMPLETELY IMMERSED IN A PERFECT AND INCOMPRESSIBLE FLUID SDLS 07‐89 ............................................................................................................................88 BENDING OF SYMMETRICAL FRAME SDLX 01‐89 ............................................................................................................................90 ASSEMBLY OF THIN RECTANGULAR SHAPED SHEETS SDLX 03‐89 ............................................................................................................................92

II.

THERMAL ........................................................................................................... 94 1.

Linear steady state thermal .................................................................................... 95 PIPE: PRESCRIBED TEMPERATURES TPLA 01‐89 ............................................................................................................................95 PIPE : PRESCRIBED TEMPERATURE, CONVECTION TPLA 02‐89 ............................................................................................................................96 PIPE : CONVECTION TPLA 03‐89 ............................................................................................................................97


no. 6

CONTENTS

POWER OUTPUT IN A PIPE TPLA 04‐89 ............................................................................................................................98 CYLINDRICAL BAR WITH FLUX DENSITY TPLA 05‐89 ............................................................................................................................99 CYLINDRICAL BAR WITH CONVECTION TPLA 06‐89 ..........................................................................................................................100 ORTHOTROPIC PIPE TPLA 07‐89 ..........................................................................................................................101 TWO‐MATERIAL PIPE : CONVECTION TPLA 08‐89 ..........................................................................................................................103 TWO‐MATERIAL PIPE : CONVECTION, THERMAL CONTACT RESISTANCE TPLA 09‐89 ..........................................................................................................................104 SIMPLE WALL : PRESCRIBED TEMPERATURES TPLL 01‐89...........................................................................................................................105 SIMPLE WALL : PRESCRIBED TEMPERATURES, CONVECTION TPLL 02‐89...........................................................................................................................106 SIMPLE WALL : CONVECTION TPLL 03‐89...........................................................................................................................107 POWER OUTPUT IN A BAR TPLL 04‐89...........................................................................................................................108 TWO‐MATERIAL WALL : CONVECTION TPLL 05‐89...........................................................................................................................109 TWO‐MATERIAL WALL : CONVECTION, THERMAL CONTACT RESISTANCE TPLL 06‐89...........................................................................................................................110 L SHAPED PLATE WITH GEOMETRIC SINGULARITY TPLP 01‐89 ..........................................................................................................................111

ORTHOTROPIC SQUARE TPLP 02‐89 ..........................................................................................................................113 HOLLOW SPHERE: PRESCRIBED TEMPERATURES TPLV 01‐89 ..........................................................................................................................115 HOLLOW SPHERE: PRESCRIBED TEMPERATURES, CONVECTION TPLV 02‐89 ..........................................................................................................................116 HOLLOW SPHERE: CONVECTION TPLV 03‐89 ..........................................................................................................................117 TWO‐MATERIAL HOLLOW SPHERE : CONVECTION TPLV 04‐89 ..........................................................................................................................118


no. 7

CONTENTS

TWO‐MATERIAL HOLLOW SPHERE: CONVECTION, THERMAL CONTACT RESISTANCE TPLV 05‐89 ..........................................................................................................................119 POWER OUTPUT IN A HOLLOW SPHERE TPLV 06‐89 ..........................................................................................................................120 ORTHOTROPIC CUBE TPLV 07‐89 ..........................................................................................................................121

2. Non linear steady state thermal ........................................................................... 123 PIPE : CONVECTION, RADIATION TPNA 01‐89 .........................................................................................................................123 SIMPLE WALL : CONVECTION, RADIATION TPNL 01‐89..........................................................................................................................124 RADIATION IN A SQUARE CAVITY TPNP 01‐89 .........................................................................................................................125 HOLLOW SPHERE: CONVECTION, RADIATION TPNV 01‐89 .........................................................................................................................126 RADIATION IN A CUBIC CAVITY TPNV 02‐89 .........................................................................................................................127

3.

Transient linear THERMAL ............................................................................... 128 CYLINDER : HEAT TRANSFER BY CONVECTION TTLA 01‐89 ..........................................................................................................................128 WALL UNDER THERMAL SHOCK TTLL 01‐89...........................................................................................................................129 PLATE : HEAT TRANSFER BY CONVECTION TTLL 02‐89...........................................................................................................................131

SPHERE : HEAT TRANSFER BY CONVECTION TTLV 01‐89 ..........................................................................................................................132

III. 1.

THERMOMECHANICS .................................................................................... 133 Linear static ......................................................................................................... 134 THICK PIPE SUBMITTED TO A THERMAL GRADIENT HSLA 03‐89..........................................................................................................................134

IV.

BIBLIOGRAPHY ............................................................................................... 135


no. 8

I.

STRUCTURAL MECHANICS


no. 9


1. Linear static EVALUATION FORM Software: SolidWorks Simulation Version: 2010 Beta2 Computer configuration used: Dell Precision T5500, Windows Vista x64 SP2, Intel Xeon quad core, 16Gb RAM, graphics card NVIDIA Quadro FX 1800. Test name: SLENDER BEAM WITH BOTH ENDS FIXED Codification: SSLL 01-89 G

A

Test performed by : Julien BOISSAT Date : 21/08/2009 Model used Finite elements  Boundary elements  Other  Element type : BEAM Number of degrees of freedom or mesh density : Nb of nodes = 135 Nb of elements = 130 Nb of DOF = 774 Results : Location

Physical quantity and reference unit

Calculated value

Deviation (%)

Shear force in G

V (N)

-540

-546

1.11

Moment in G

M (Nm)

2800

2800

0

Displacement in G

v (m)

- 4.90 × 10-2

- 4.92 × 10 -2

0.04

Axial force in A

H (N)

- 24000

- 24000

0

Comments :


no. 10

STRUCTURAL MECHANICS EVALUATION FORM Software: SolidWorks Simulation Version: 2010 PR2 Computer configuration used: Dell Precision T5500, Windows Vista x64 SP2, Intel Xeon quad core, 16Gb RAM, graphics card NVIDIA Quadro FX 1800. Test name: SLENDER BEAM ON THREE SIMPLE SUPPORTS Codification: SSLL 03-89

B



Calculated value

Deviation (%)

Moment in B

M (Nm)

± 63000

± 62960

0

Displacement in B

v (m)

- 0.010

- 0.010

0

Reaction force in B

V (N)

21000

21000

0

Comments : The vertical beam was modeled in order to simulate the elastic support.


no. 11

STRUCTURAL MECHANICS EVALUATION FORM Software: SolidWorks Simulation Version: 2010 PR2 Computer configuration used: Dell Precision T5500, Windows Vista x64 SP2, Intel Xeon quad core, 16Gb RAM, graphics card NVIDIA Quadro FX 1800. Test name: BIMETALLIC STRIP FIXED ON BOTH ENDS CONNECTED WITH A RIGID BAR Codification: SSLL 05-89

B A

C D Test performed by : Julien BOISSAT Date : 21/08/2009 Model used Finite elements  Boundary elements  Other  Element type : BEAM Number of degrees of freedom or mesh density : Nb of nodes = 357 Nb of elements = 353 Nb of DOF = 2112 Results : Physical quantity and Calculated Location reference unit value

Deviation(%)

B

v (m)

-0.125

-0.123

1.6

D

v (m)

-0.125

-0.123

1.6

A

V (N)

500

500

0

A

M (Nm)

500

497.5

0.5

C

V (N)

500

500

0

C

M (Nm)

500

497.5

0.5

Comments :


no. 12

STRUCTURAL MECHANICS EVALUATION FORM Software: SolidWorks Simulation Version: 2010 Beta2 Computer configuration used: Dell Precision T5500, Windows Vista x64 SP2, Intel Xeon quad core, 16Gb RAM, graphics card NVIDIA Quadro FX 1800. Test name: FIXED THIN ARC UNDER INPLANE BENDING Codification: SSLL 06-89

B


B

Physical quantity and reference unit u (m) 0.3791 v (m) 0.2417 θ (rad) 0.1654

Calculated value 0.3791 0.2417 0.1654

Deviation (%)

0 0 0

Comments :


no. 13

STRUCTURAL MECHANICS EVALUATION FORM Software: SolidWorks Simulation Version: 2010 Beta2 Computer configuration used: Dell Precision T5500, Windows Vista x64 SP2, Intel Xeon quad core, 16Gb RAM, graphics card NVIDIA Quadro FX 1800. Test name: FIXED THIN ARC UNDER OUT OF PLANE BENDING Codification: SSLL 07-89

15°

B

Test performed by : Julien BOISSAT Date : 21/08/2009 Model used Finite elements  Boundary elements  Other  Element type : BEAMS Number of degrees of freedom or mesh density : Nb of nodes = 539 Nb of elements = 269 Nb of DOF = 1614 Results : Location


Calculated value

Deviation(%)

B

u B (m)

0.13462

0.1346

0

For θ = 15°

M t (Nm) M f (Nm)

74.1180 - 96.5925

74.12* -96.595*

0 0

Comments : * : Obtained by averaging the values of two neighboring elements


no. 14

STRUCTURAL MECHANICS EVALUATION FORM Software: SolidWorks Simulation Version: 2010 PR1 Computer configuration used: Dell Precision T5500, Windows Vista x64 SP2, Intel Xeon quad core, 16Gb RAM, graphics card NVIDIA Quadro FX 1800. Test name: SIMPLY SUPPORTED THIN ARC UNDER INPLANE BENDING Codification: SSLL 08-89

Test performed by : Julien BOISSAT Date : 22/09/2009 Model used Finite elements  Boundary elements  Other  Element type : BEAM Number of degrees of freedom or mesh density : Nb of nodes = 561 Nb of elements = 280 Nb of DOF = 1683 Results : Physical quantity and Location Calculated value reference unit A B C B

θ A (rad) θ B (rad) vC (m) u B (m)

-3.0774 × 10 -2 3.0774 × 10 -2 -1.9206 × 10 -2 5.3912 × 10 -2

-3.079 × 10 -2 3.079 × 10 -2 -1.921 × 10 -2 5.39 × 10-2

Deviation (%)

0.05 0.05 0.02 0.02

Comments :


no. 15

STRUCTURAL MECHANICS EVALUATION FORM Software: SolidWorks Simulation Version: 2010 PR1 Computer configuration used: Dell Precision T5500, Windows Vista x64 SP2, Intel Xeon quad core, 16Gb RAM, graphics card NVIDIA Quadro FX 1800. Test name: TWO BAR SYSTEM WITH THREE UNIVERSAL JOINTS Codification: SSLL 09-89

Test performed by : Julien BOISSAT Date : 22/09/2009 Model used Finite elements  Boundary elements  Other  Element type : BAR Number of degrees of freedom or mesh density : Nb of nodes =5 Nb of elements = 2 Nb of DOF =3 Results : Location

C Bar AC Bar BC

Physical quantity and reference unit vC (m) -3 × 10-3 σ (Pa) 7 × 10 7 σ (Pa) 7 × 10 7

Calculated value

Deviation(%)

-3 × 10-3 7 × 107 7 × 107

0 0 0

Comments :


no. 16

STRUCTURAL MECHANICS EVALUATION FORM Software: SolidWorks Simulation Version: 2010 PR1 Computer configuration used: Dell Precision T5500, Windows Vista x64 SP2, Intel Xeon quad core, 16Gb RAM, graphics card NVIDIA Quadro FX 1800. Test name: FRAME WITH LATERAL CONNECTIONS Codification: SSLL 10-89

D

C

A

B

E

Test performed by : Julien BOISSAT Date : 22/09/2009 Model used Finite elements  Boundary elements  Other  Element type : BEAM Number of degrees of freedom or mesh density : Nb of nodes = 417 Nb of elements = 411 Nb of DOF = 2451 Results : Physical quantity and Location Calculated value reference unit A θ (rad) 0.227118 0.2274 M AB (Nm) 11023.72 11021 A A M AC (Nm) 113.559 113.7 M AD (Nm) -12348.588 -12350 A A M AE (Nm) 1211.2994 1213

Deviation (%)

0.12 0.02 0.12 0.01 0.13

Comments :


no. 17

STRUCTURAL MECHANICS EVALUATION FORM Software: SolidWorks Simulation Version: 2010 PR1 Computer configuration used: Dell Precision T5500, Windows Vista x64 SP2, Intel Xeon quad core, 16Gb RAM, graphics card NVIDIA Quadro FX 1800. Test name: FRAMEWORK OF ARTICULATED BASR UNDER CONCENTRATED LOAD Codification: SSLL 11-89 D

C

Test performed by : Julien BOISSAT Date : 22/09/2009 Model used Finite elements  Boundary elements  Other  Element type : BAR Number of degrees of freedom or mesh density : Nb of nodes =8 Nb of elements = 4 Nb of DOF =6 Results : Location

C C D D

Physical quantity and reference unit uC (m) 0.26517 × 10 -3 vC (m) 0.08839 × 10 -3

u D (m) v D (m)

3.47902 × 10 -3 -5.60084 × 10 -3

Calculated value

Deviation(%)

0.2652 × 10 -3 0.08839 × 10 -3 3.479 × 10 -3 -5.6 × 10-3

0.01 0 0 0.02

Comments :


no. 18

STRUCTURAL MECHANICS EVALUATION FORM Software: SolidWorks Simulation Version: 2010 PR1 Computer configuration used: Dell Precision T5500, Windows Vista x64 SP2, Intel Xeon quad core, 16Gb RAM, graphics card NVIDIA Quadro FX 1800. Test name: PRE-STRESSED BAR Codification: SSLL 13-89

D H

E C

Test performed by : Julien BOISSAT Date : 22/09/2009 Model used Finite elements  Boundary elements  Other  Element type : BEAMS Number of degrees of freedom or mesh density : Nb of nodes = 201 Nb of elements = 196 Nb of DOF = 1170 Results : Location

CE H D


N , traction force (N) M , bending moment (Nm) v D (m)

Calculated value

Deviation (%)

584584

585244

0.11

49249.5

48854

0.8

-0.0005428

-0.0005562

2.4

Comments :


no. 19

STRUCTURAL MECHANICS EVALUATION FORM Software: SolidWorks Simulation Version: 2010 PR1 Computer configuration used: Dell Precision T5500, Windows Vista x64 SP2, Intel Xeon quad core, 16Gb RAM, graphics card NVIDIA Quadro FX 1800. Test name: SIMPLY SUPPORTED PLANAR FRAME Codification: SSLL 14-89

C

A


A A C

Calculated value

Deviation( %)

31500.0

31500

0

20239.4

20240

0

-0.03072

-0.03079

0.22


V , vertical reaction (N) H , horizontal reaction (N) vC (m)

Comments :


no. 20

STRUCTURAL MECHANICS EVALUATION FORM Software: SolidWorks Simulation Version: 2010 PR1 Computer configuration used: Dell Precision T5500, Windows Vista x64 SP2, Intel Xeon quad core, 16Gb RAM, graphics card NVIDIA Quadro FX 1800. Test name: PLATE UNDER BENDING AND SHEAR IN I TS OWN PLANE Codification: SSLP 01-89

Test performed by : Julien BOISSAT Date : 22/09/2009 Model used Finite elements  Boundary elements  Other  Element type : SHELL 6 Number of degrees of freedom or mesh density : Nb of nodes = 5414 Nb of elements = 2603 Nb of DOF = 32274 Results : Physical Reference Calculated Location quantity value value ( L,y) v1 0.3413 0.3557 ( L,y) v2 0.3573 0. 3564


Deviation (%)

4.22 0.22

no. 21


Comments :


no. 22

STRUCTURAL MECHANICS EVALUATION FORM Software: SolidWorks Simulation Version: 2010 PR1 Computer configuration used: Dell Precision T5500, Windows Vista x64 SP2, Intel Xeon quad core, 16Gb RAM, graphics card NVIDIA Quadro FX 1800. Test name: PERFORATED PLATE UNDER SIMPLE TRACTION Codification: SSLP 02-89

Test performed by : Julien BOISSAT Date : 22/09/2009 Model used Finite elements  Boundary elements  Other  Element type : SHELL 6 Number of degrees of freedom or mesh density : Nb of nodes = 7168 Nb of elements = 3424 Nb of DOF = 42444 Results : Location (Space-Time) (a,0) (a,π /4) (a,π / 2)

Physical quantity (unit) σ θθ (N/mm2) σ θθ (N/mm2) σ θθ (N/mm2)

Reference value 7.5 2.5 -2.5

Calculated value 7.588 2.511 -2.559

Deviation (%)

1.12 0.44 2.4

Comments : The formulas of the analytical solution are solely applicable when the length and width of the sheet are large enough compared to the diameter of the hole. The stresses away from the hole should not be affected by its presence. With the given dimensions, the ratio between the diameter and the width is equal to 0.2 which is not enough. For the formulas to be applicable, the plate should be at least 4 times larger (ratio equal to 0.05). The values in the table above are given for such a modified geometry.


no. 23

STRUCTURAL MECHANICS EVALUATION FORM Software: SolidWorks Simulation Version: 2010 PR1 Computer configuration used: Dell Precision T5500, Windows Vista x64 SP2, Intel Xeon quad core, 16Gb RAM, graphics card NVIDIA Quadro FX 1800. Test name: CANTILEVER RECTANGULAR PLATE Codification: SSLS 01-89

Test performed by : Julien BOISSAT Date : 22/09/2009 Model used Finite elements  Boundary elements  Other  Element type : SHELL 6 Number of degrees of freedom or mesh density : Nb of nodes = 10467 Nb of elements = 5058 Nb of DOF = 62604 Results : Location

Side x = 1

Physical quantity w (m)

Reference value

Calculated value

Deviation (%)

-0.0973

-0.0958

1.57

Comments :


no. 24

STRUCTURAL MECHANICS EVALUATION FORM Software: SolidWorks Simulation Version: 2010 PR1 Computer configuration used: Dell Precision T5500, Windows Vista x64 SP2, Intel Xeon quad core, 16Gb RAM, graphics card NVIDIA Quadro FX 1800. Test name: SIMPLY SUPPORTED SQUARE PLATE Codification: SSLS 02-89

Test performed by : Julien BOISSAT Date: 23/09/2009 Model used Finite elements  Boundary elements  Other  Element type : SHELL 6 Number of degrees of freedom or mesh density : Nb of nodes = 4505 Nb of elements = 2184 Nb of DOF = 27030 Results : Location

Physical quantity wO (m)

Reference (1) value -0.1649 × 10-3

Calculated value -0.1648× 10-3

Deviation (%)

Center O 0.01 Comments : (1) "Roark’s Formulas for Stress & Strain" (6 th ed. p.458) gives the following formula for a thin simply supported square plate : − α qb 4 Max y = where b is the width, a is the length, t the thickness and α = -0.0444 for Et 3 b =1 which gives a maximum displacement ymax = -0.1649 × 10 -3m. a


no. 25

STRUCTURAL MECHANICS EVALUATION FORM Software: SolidWorks Simulation Version: 2010 PR1 Computer configuration used: Dell Precision T5500, Windows Vista x64 SP2, Intel Xeon quad core, 16Gb RAM, graphics card NVIDIA Quadro FX 1800. Test name: CIRCULAR PLATE UNDER UNIFORM PRESSURE LOAD Codification: SSLS 03-89


Center O

Physical quantity wO (m)

Reference value -0.0065

Calculated value -0.0065

Deviation (%)

0

Comments :


no. 26

STRUCTURAL MECHANICS EVALUATION FORM Software: SolidWorks Simulation Version: 2010 PR1 Computer configuration used: Dell Precision T5500, Windows Vista x64 SP2, Intel Xeon quad core, 16Gb RAM, graphics card NVIDIA Quadro FX 1800. Test name: RECTANGULAR HOLLOW BEAM UNDER TORSION Codification: SSLS 05-89

A

B

Test performed by : Julien BOISSAT Date: 23/09/2009 Model used Finite elements  Boundary elements  Other  Element type : SHELL 6 Number of degrees of freedom or mesh density : Nb of nodes = 10304 Nb of elements = 5120 Nb of DOF = 61440 Results : Location (Space-Time) Point A (0.5,0,0.05)

Point B (0.8,-0.05,0)

Physical quantity (unit) v (m) θ x (rad) σ xy (Pa) w (m) θ x (rad) σ xy (Pa) (1)

Reference value -0.617 × 10 -6 0.123 × 10 -4 -0.11 × 10 6 -0.987 × 10 -6 0.197 × 10 -4 -0.11 × 10 6

Calculated value -0.616 × 10 -6 0.123 × 10 -4 -0.1096 × 10 6 -0.987 × 10 -6 0.197 × 10 -4 -0.1096 × 10 6

Deviation (%) 0.16 0 0.36 0 0 0.36

Comments : (1) A typo was detected in the Guide: at point B, the table should read σ xz instead of σ xy.


no. 27

STRUCTURAL MECHANICS EVALUATION FORM Software: SolidWorks Simulation Version: 2010 PR1 Computer configuration used: Dell Precision T5500, Windows Vista x64 SP2, Intel Xeon quad core, 16Gb RAM, graphics card NVIDIA Quadro FX 1800. Test name: THIN CYLINDER UNDER UNIFORM RADIAL PRESSURE Codification: SSLS 06-89


All points

Physical quantity σ 11 (Pa) σ 22 (Pa) δ R (m) δ L (m)

Reference value 0.0 5.00 × 105 2.38 × 10 -6 -2.86 × 10-6

Calculated value 500 (1) 4.97 × 10 5 2.38 × 10-6 -2.87 × 10-6

Deviation (%)

0.6 0 0.35

Comments : (1) σ 11 = 500 Pa should be compared to the load and/or to σ 22 . The result is acceptable (ratio equal to 1/1000).


no. 28

STRUCTURAL MECHANICS EVALUATION FORM Software: SolidWorks Simulation Version: 2010 PR1 Computer configuration used: Dell Precision T5500, Windows Vista x64 SP2, Intel Xeon quad core, 16Gb RAM, graphics card NVIDIA Quadro FX 1800. Test name: THIN CYLINDER UNDER UNIFORM AXIAL PRESSURE Codification: SSLS 07-89


All points

Physical quantity σ 11 (Pa) σ 22 (Pa) δ L (m) δ R (m)

Reference value 5.00 × 105 0.0 9.52 × 10 -6 -7.14 × 10-7

Calculated value 4.99 × 105 106 (1) 9.525 × 10 -6 -7.159 × 10 -7

Deviation (%)

0.2 0.05 0.26

Comments : (1) σ 22 = 106 Pa should be compared to the load and/or to σ 11 . The result is acceptable (ratio smaller than 1/1000).


no. 29

STRUCTURAL MECHANICS EVALUATION FORM Software: SolidWorks Simulation Version: 2010 PR1 Computer configuration used: Dell Precision T5500, Windows Vista x64 SP2, Intel Xeon quad core, 16Gb RAM, graphics card NVIDIA Quadro FX 1800. Test name: THIN CYLINDER UNDER HYDROSTATIC PRESSURE Codification: SSLS 08-89

Test performed by : Julien BOISSAT Date: 24/09/2009 Model used Finite elements  Boundary elements  Other  Element type : SHELL 6 Number of degrees of freedom or mesh density : Nb of nodes = 4600 Nb of elements = 2256 Nb of DOF = 27600 Results : Physical Reference Calculated Location quantity value value σ 11 (Pa) 0.0 100 (1) ∀ x σ 22 (Pa) 5.00 × 105 4.99 × 105 x = L/2 δ R (m) 2.38 × 10 -6 2.37 × 10 -6 x = L/2 δ L (m) -2.86 × 10-6 -2.86 × 10-6 x = L ψ (rad) 1.19 × 10 -6 1.185 × 10 -6

Deviation (%)

0.2 0.42 0 0.42

Comments : (1) σ 11 = 100 Pa should be compared to the load and/or to the calculated stress σ 22 . The result is acceptable (ratio smaller than 1/1000).


no. 30

STRUCTURAL MECHANICS EVALUATION FORM Software: SolidWorks Simulation Version: 2010 PR1 Computer configuration used: Dell Precision T5500, Windows Vista x64 SP2, Intel Xeon quad core, 16Gb RAM, graphics card NVIDIA Quadro FX 1800. Test name: THIN CYLINDER UNDER ITS OWN WEIGHT Codification: SSLS 09-89


∀ x x = L

Physical quantity σ 22 (Pa) σ 11 (Pa) δ x (m) δ R (m) ψ (rad)

Reference value 0.0 3.14 × 105 2.99 × 10 -6 -4.49 × 10-7 -1.12 × 10-7

Calculated value 110 1 3.14 × 10 5 2.99 × 10 -6 -4.49 × 10 -7 -1.16 × 10 -7

Deviation (%)

0 0 0 3.57

Comments : (1) σ 22 = 110 Pa should be compared to the load and/or to σ 11. The result is acceptable (ratio equal to 1/1000).


no. 31

STRUCTURAL MECHANICS EVALUATION FORM Software: SolidWorks Simulation Version: 2010 PR1 Computer configuration used: Dell Precision T5500, Windows Vista x64 SP2, Intel Xeon quad core, 16Gb RAM, graphics card NVIDIA Quadro FX 1800. Test name: TORE UNDER INTERNAL UNIFORM PRESSURE Codification: SSLS 10-89

Test performed by : Julien BOISSAT Date: 24/09/2009 Model used Finite elements  Boundary elements  Other  Element type : SHELL 6 Number of degrees of freedom or mesh density : Nb of nodes = 4672 Nb of elements = 2288 Nb of DOF = 28032 Results : Location (Space-Time) For every r r=a–b r=a+b

Physical quantity (unit) σ 22 (Pa) σ 11 (Pa) δr (m) σ 11 (Pa) δr (m)

Reference value 2.5 × 105 7.5 × 105 1.19 × 10-7 4.17 × 10 5 1.79 × 10 -6

Calculated value 2.51 × 105 7.46 × 105 1.20 × 10 -7 4.14 × 105 1.77 × 10 -6

Deviation (%) 0.40 0.54 0.84 0.72 1.12

Comments :


no. 32

STRUCTURAL MECHANICS EVALUATION FORM Software: SolidWorks Simulation Version: 2010 PR1 Computer configuration used: Dell Precision T5500, Windows Vista x64 SP2, Intel Xeon quad core, 16Gb RAM, graphics card NVIDIA Quadro FX 1800. Test name: SPHERICAL CAP UNDER INTERNAL PRESSURE Codification: SSLS 14-89


Physical quantity

For every θ θ = 90°

σ 11 = σ 22 (Pa) δ R (m)

Reference value 2.50 × 10 5 8.33 × 10 -7

Calculated value 2.50 × 105 8.33 × 10-7

Deviation (%) 0 0

Comments :


no. 33

STRUCTURAL MECHANICS EVALUATION FORM Software: SolidWorks Simulation Version: 2010 PR1 Computer configuration used: Dell Precision T5500, Windows Vista x64 SP2, Intel Xeon quad core, 16Gb RAM, graphics card NVIDIA Quadro FX 1800. Test name: SPHERICAL CAP UNDER RADIAL FORCE Codification: SSLS 15-89


Mid-surface On external plane

Physical quantity

Reference value

Calculated value

Deviation (%)

σ 11 (Pa) σ 22 (Pa) δ R (m)

0 9.09 × 10 5 4.33 × 10 -6

132 9.08 × 10 5 4.33 × 10 -6

0.11 0

Comments :


no. 34

STRUCTURAL MECHANICS EVALUATION FORM Software: SolidWorks Simulation Version: 2010 PR1 Computer configuration used: Dell Precision T5500, Windows Vista x64 SP2, Intel Xeon quad core, 16Gb RAM, graphics card NVIDIA Quadro FX 1800. Test name: SPHERICAL CAP UNDER MOMENT Codification: SSLS 16-89

Test performed by : Julien BOISSAT Date: 24/09/2009 Model used Finite elements  Boundary elements  Other  Element type : SHELL 6 Number of degrees of freedom or mesh density : Nb of nodes = 3130 Nb of elements = 1459 Nb of DOF = 18777 Results :

On the extremity

Physical quantity σ 22 (Pa) δ R (m)

Reference value 8.26 × 105 3.93 × 10 -6

Calculated value 8.18 × 10 5 3.93 × 10 -6

External plane

σ 22 (Pa)

3.76 × 105 (1)

3.75 × 105

Location

Deviation (%)

0.96 0 0.26

Comments :


no. 35

STRUCTURAL MECHANICS EVALUATION FORM Software: SolidWorks Simulation Version: 2010 PR1 Computer configuration used: Dell Precision T5500, Windows Vista x64 SP2, Intel Xeon quad core, 16Gb RAM, graphics card NVIDIA Quadro FX 1800. Test name: SPHERICAL CAP UNDER ITS OWN WEIGHT Codification: SSLS 17-89

Test performed by : Julien BOISSAT Date: 28/09/2009 Model used Finite elements  Boundary elements  Other  Element type : SHELL 6 Number of degrees of freedom or mesh density : Nb of nodes = 4607 Nb of elements = 2240 Nb of DOF = 27639 Results : Physical Reference Calculated Location quantity value value 4 σ 11 (Pa) 7.85 × 10 7.79 × 104 θ = 90° σ 22 (Pa) -7.85 × 104 -7.85 × 104 δ R (m) 4.86 × 10 -7 4.88 × 10 -7

Deviation (%)

0.77 0 0.41

Comments :


no. 36

STRUCTURAL MECHANICS EVALUATION FORM Software: SolidWorks Simulation Version: 2010 PR1 Computer configuration used: Dell Precision T5500, Windows Vista x64 SP2, Intel Xeon quad core, 16Gb RAM, graphics card NVIDIA Quadro FX 1800. Test name: SPHERICAL CAP UNDER IMPOSED DISPLACEMENT Codification: SSLS 18-89

Test performed by : Julien BOISSAT Date: 28/09/2009 Model used Finite elements  Boundary elements  Other  Element type : SHELL 6 Number of degrees of freedom or mesh density : Nb of nodes = 4607 Nb of elements = 2240 Nb of DOF = 27378 Results : Physical Reference Calculated Location quantity value value 4 V 1 (N) per radian 4.62 × 10 4.64 × 104 On the σ 11 (Pa) 0.0 6.9 × 104 (1) extremity σ 22 (Pa) 2.1 × 107 2.1 × 107 σ 11 (Pa) 3.81 × 10 7 3.79 × 107 External plane σ 22 (Pa) 3.24 × 10 7 3.32 × 107

Deviation (%)

0.4 0 0.79 2.47

Comments : (1) Compared to σ 22 , σ 11 is negligible.


no. 37

STRUCTURAL MECHANICS EVALUATION FORM Software: SolidWorks Simulation Version: 2010 PR1 Computer configuration used: Dell Precision T5500, Windows Vista x64 SP2, Intel Xeon quad core, 16Gb RAM, graphics card NVIDIA Quadro FX 1800. Test name: CYLINDRICAL SHELL UNDER ITS OWN WEIGHT Codification: SSLS 19-89

B


B

Physical quantity w B (m)

Reference value -3.70 × 10-2

Calculated value -3.6× 10-2

Deviation (%)

2.78

Comments : In the Guide, the unit of γ was interpreted as N/m3 instead of kg/m3.


no. 38

STRUCTURAL MECHANICS EVALUATION FORM Software: SolidWorks Simulation Version: 2010 PR1 Computer configuration used: Dell Precision T5500, Windows Vista x64 SP2, Intel Xeon quad core, 16Gb RAM, graphics card NVIDIA Quadro FX 1800. Test name: PINCHED CYLINDRICAL SHELL Codification: SSLS 20-89


Physical quantity

Reference value

Calculated value

Deviation (%)

A

v (m) , displacement in y

-113.9 × 10-3

-113.7 × 10-3

0.18

Comments :


no. 39

STRUCTURAL MECHANICS EVALUATION FORM Software: SolidWorks Simulation Version: 2010 PR1 Computer configuration used: Dell Precision T5500, Windows Vista x64 SP2, Intel Xeon quad core, 16Gb RAM, graphics card NVIDIA Quadro FX 1800. Test name: SPHERICAL SHELL WITH HOLE Codification: SSLS 21-89


A(R,0,0)

Physical quantity u A (m) , displacement in x

Reference value

Calculated value

Deviation (%)

94.0 × 10-3

96.8 × 10-3

2.89

Comments :


no. 40

STRUCTURAL MECHANICS EVALUATION FORM Software: SolidWorks Simulation Version: 2010 PR1 Computer configuration used: Dell Precision T5500, Windows Vista x64 SP2, Intel Xeon quad core, 16Gb RAM, graphics card NVIDIA Quadro FX 1800. Test name: SPHERICAL CAP UNDER EXTERNAL UNIFORM PRESSURE Codification: SSLS 22-89

Test performed by : Julien BOISSAT Date: 29/09/2009 Model used Finite elements  Boundary elements  Other  Element type : SHELL 6 Number of degrees of freedom or mesh density : Nb of nodes = 10347 Nb of elements = 4978 Nb of DOF = 61785 Results : Reference Calculated Location Physical quantity value value -3 ψ = 15° u (m), -1.73 × 10 -1.77× 10-3 ψ = 45° horizontal -1.02 × 10 -3 -1.02× 10-3 ψ = 15° σ (Pa), external -0.74 × 10 8 -0.69 × 10 8 ψ = 45° meridian -0.68 × 10 -0.68 × 10 8

Deviation (%) 2.31 0 7.25 0

Comments :


no. 41

STRUCTURAL MECHANICS EVALUATION FORM Software: SolidWorks Simulation Version: 2010 PR1 Computer configuration used: Dell Precision T5500, Windows Vista x64 SP2, Intel Xeon quad core, 16Gb RAM, graphics card c ard NVIDIA Quadro FX 1800. Test name: CYLINDRICAL MEMBRANE UNDER BENDING Codification: SSLS 23-89

E

Test performed by : Julien BOISSAT Date: 29/09/2009 Model used Finite elements  Boundary elements  Other  Element type : SHELL 6 Number of degrees of freedom or mesh density : First and second load Nb of nodes = 4473 Nb of elements = 2168 Nb of DOF = 26436 Results : Location

Physical quantity

Reference value

Point E Point E

circumferential stress on external skin (MPa)

60

Calculated value

Deviation (%)

59.993

0.12

59.87

0.18

Comments :


no. 42

STRUCTURAL MECHANICS EVALUATION FORM Software: SolidWorks Simulation Version: 2010 PR1 Computer configuration used: Dell Precision T5500, Windows Vista x64 SP2, Intel Xeon quad core, 16Gb RAM, graphics card c ard NVIDIA Quadro FX 1800. Test name: SIMPLY SUPPORTED RECTANGULAR PLATE UNDER UNIFORM PRESSURE Codification: SSLS 24-89

A Test performed by : Julien BOISSAT Date: 29/09/2009 Model used Finite elements  Boundary elements  Other  Element type : SHELL 6 Number of degrees of freedom or mesh density : b/a = b/a = 1 b/a = b/a = 2 b/a = b/a = 5 Nb of nodes = 4569 Nb of nodes = 4709 Nb of nodes = 4499 Nb of elements = 2216 Nb of elements = 2282 Nb of elements = 2158 Nb of DOF = 27411 Nb of DOF = 28251 Nb of DOF = 26991 Results : Physical Reference Calculated Deviation (%) Location (1) quantity value value 0.0443 0.0444 0.23 α b/a = b/a = 1.0 β 0.0479 0.0479 0 0.0479 0.0479 0 β 1 0.1106 0.1106 0 α b/a = b/a = 2.0 β 0.1017 0.1017 0 0.0464 0.0465 0.22 β 1 0.1416 0.1417 0.07 α b/a = b/a = 5.0 β 0.1246 0.1245 0.08 β 1 0.0375 0.0376 0.27 Comments : (1) Values α, β and β and β 1 are calculated from the values of wmax, σ x max, σ y max and the following 6 M α pa 4 2 2 = M β pa M β pa = = σ formulas : w max = , and and . x max y max 1 Flex h² Eh 3


no. 43

STRUCTURAL MECHANICS EVALUATION FORM Software: SolidWorks Simulation Version: 2010 PR1 Computer configuration used: Dell Precision Prec ision T5500, Windows Vista x64 SP2, Intel Xeon quad core, 16Gb RAM, graphics card ca rd NVIDIA Quadro FX 1800. Test name: SIMPLY SUPPORTED RHOMB PLATE UNDER BENDING Codification: SSLS 25-89

Test performed by : Julien BOISSAT Date: 29/09/2009 Model used Finite elements  Boundary elements  Other  Element type : SHELL 6 Number of degrees of freedom or mesh density : α = 80° α = 60° α = 40° α = 30° N. of nodes = 4657 N. of nodes = 4617 N. of nodes = 4701 N. of nodes = 4729 N. of elements=2260 N. of elements=2236 N. of elements=2266 N. of elements = 2268 N. of DOF = 27942 N. of DOF = 27702 N. of DOF = 28206 N. of DOF = 28374 Results : Location

α = 80° α = 60° α = 40° α = 30°

Physical quantity

wC (mm)

Reference value 1.409 × 10 -3 0.9318 × 10 -3 0.3487 × 10 -3 0.1485 × 10 -3

Calculated value 1.409 × 10 -3 0.9323 × 10 -3 0.3507 × 10 -3 0.1503 × 10 -3

Deviation (%)

0 0.05 0.57 1.21

Comments : A typo in the guide was corrected: E = 30 × 10 6 Pa instead of 36 × 10 6


no. 44

STRUCTURAL MECHANICS EVALUATION FORM Software: SolidWorks Simulation Version: 2010 PR1 Computer configuration used: Dell Precision T5500, Windows Vista x64 SP2, Intel Xeon quad core, 16Gb RAM, graphics card NVIDIA Quadro FX 1800. Test name: PLATE UNDER NORMAL SHEAR Codification: SSLS 27-89

C


Physical quantity

Reference value

Calculated value

Deviation (%)

Point C

Displacement w (m)

35.37 × 10 -3

35.29 × 10 -3

0.23

Comments :


no. 45

STRUCTURAL MECHANICS EVALUATION FORM Software: SolidWorks Simulation Version: 2010 PR1 Computer configuration used: Dell Precision T5500, Windows Vista x64 SP2, Intel Xeon quad core, 16Gb RAM, graphics card NVIDIA Quadro FX 1800. Test name: FULL CYLINDER UNDER SIMPLE TRACTION Codification: SSLV 01-89

F

E D A

B C

Test performed by : Julien BOISSAT Date: 29/09/2009 Model used Finite elements  Boundary elements  Other  Element type : TETRA 10 Number of degrees of freedom or mesh density : Nb of nodes = 3188 Nb of elements = 1915 Nb of DOF = 9561 Results : Physical Reference Calculated Location quantity value value point A u A (m) 1.5 × 10-3 1.5 × 10-3 point B u B (m) 1.5 × 10-3 1.5 × 10-3 point C uC (m) 1.5 × 10-3 1.5 × 10-3 point D u D (m) 1 × 10-3 1 × 10-3 point E u E (m) 0.5 × 10-3 0.5 × 10-3 point A w A (m) -0.15 × 10-3 -0.15 × 10 -3 point D w D (m) -0.15 × 10-3 -0.15 × 10 -3 point E w E (m) -0.15 × 10-3 -0.15 × 10 -3 point F w F (m) -0.15 × 10-3 -0.15 × 10 -3

Deviation (%) 0 0 0 0 0 0 0 0 0

Comments :


no. 46

STRUCTURAL MECHANICS EVALUATION FORM Software: SolidWorks Simulation Version: 2010 PR1 Computer configuration used: Dell Precision T5500, Windows Vista x64 SP2, Intel Xeon quad core, 16Gb RAM, graphics card NVIDIA Quadro FX 1800. Test name: FULL SPHERE UNDER UNIFORM PRESSURE Codification: SSLV 02-89

Test performed by : Julien BOISSAT Date: 09/10/2009 Model used Finite elements  Boundary elements  Other  Element type : TETRA 10 Number of degrees of freedom or mesh density : Nb of nodes = 24086 Nb of elements = 16357 Nb of DOF = 72255 Results : Reference Calculated Location Physical quantity value value point A σ x (MPa) -100 -100.18 point B σ (MPa) -100 -99.86 point C σ z (MPa) -100 -100.05 -3 point A u A (m) -0.2 × 10 -0.2 × 10-3 point B v B (m) -0.2 × 10-3 -0.2 × 10-3 point C wC (m) -0.2 × 10-3 -0.2 × 10-3 point A’ σ x (MPa) -100 -99.99 point B’ σ (MPa) -100 -100.0 point C’ σ z (MPa) -100 -100.01 -3 point A’ u A’ (m) -0.1 × 10 -0.9999 × 10-3 point B’ u B’ (m) -0.1 × 10 -3 -0.1 × 10-3 point C’ uC’ (m) -0.1 × 10-3 -0.1 × 10-3

Deviation (%) 0.12 0.24 0.05 0 0 0 0.07 0 0.01 0.01 0 0

Comments :


no. 47

STRUCTURAL MECHANICS EVALUATION FORM Software: SolidWorks Simulation Version: 2010 PR1 Computer configuration used: Dell Precision T5500, Windows Vista x64 SP2, Intel Xeon quad core, 16Gb RAM, graphics card NVIDIA Quadro FX 1800. Test name: THICK SPHERICAL TANK UNDER INTERNAL PRESSURE Codification: SSLV 03-89

Test performed by : Julien BOISSAT Date: 09/10/2009 Model used Finite elements  Boundary elements  Other  Element type : TETRA 10 Number of degrees of freedom or mesh density : Nb of nodes = 11265 Nb of elements = 7439 Nb of DOF = 33795 Results : Location

Internal edge r = a External edge r=b

Physical quantity σ rr (MPa) σ θθ (MPa) u (m) σ rr (MPa) σ θθ (MPa) u (m)

Reference value

-100 71.43 0.4 × 10-3 0 21.43 1.5 × 10-4

Calculated value -99.21 71.42 0.4004 × 10 -3 0.048 21.43 1.5 × 10-4

Deviatio n (%) 0.79 0 0.1 0 0

Comments :


no. 48

STRUCTURAL MECHANICS EVALUATION FORM Software: SolidWorks Simulation Version: 2010 PR1 Computer configuration used: Dell Precision T5500, Windows Vista x64 SP2, Intel Xeon quad core, 16Gb RAM, graphics card NVIDIA Quadro FX 1800. Test name: THICK INFINITE PIPE UNDER INTERNAL PRESSURE Codification: SSLV 04-89

Test performed by : Julien BOISSAT Date: 09/10/2009 Model used Finite elements  Boundary elements  Other  Element type : TETRA 10 Number of degrees of freedom or mesh density : Nb of nodes = 11947 Nb of elements = 7872 Nb of DOF = 35841 Results : Physical Reference Calculated Location quantity value value σ r (MPa) -60 -59.73 σ θ (MPa) 100 99.96 Internal wall τ max (MPa) 80 80.25 -6 ur (m) 59 × 10 59 × 10-6 σ r (MPa) 0 0.02 σ θ (MPa) 40 40 External wall τ max (MPa) 20 20.01 -6 ur (m) 40 × 10 40 × 10-6

Deviation (%) 0.45 0.04 0.31 0 0 0.05 0

Comments :


no. 49

STRUCTURAL MECHANICS EVALUATION FORM Software: SolidWorks Simulation Version: 2010 PR1 Computer configuration used: Dell Precision T5500, Windows Vista x64 SP2, Intel Xeon quad core, 16Gb RAM, graphics card NVIDIA Quadro FX 1800. Test name: BEAM WITH ELLIPTIC CROSS SECTION UNDER TORSION Codification: SSLV 05-89

A

C B

Test performed by : Julien BOISSAT Date: 09/10/2009 Model used Finite elements  Boundary elements  Other  Element type : TETRA 10 Number of degrees of freedom or mesh density : Nb of nodes = 10467 Nb of elements = 6604 Nb of DOF = 30930 Results : Calculated Location Physical quantity Reference value value σ xy (MPa) -39.5 -39.65 σ xz (MPa) 0 0 σ xθ (MPa) 39.5 39.65 Point A u (m) 0 0 -3 v (m) -2.57 × 10 -2.49 × 10 -3 w (m) 0 0 σ xy (MPa) 0 0 σ xz (MPa) 19.8 19.74 σ xθ (MPa) 19.8 19.74 Point B u (m) 0 0 v (m) 0 0 -3 (1) w (m) 4.97 × 10 4.98 × 10-3 Point C u (m) -9.6 × 10-5 -9.64 × 10 -5

Deviatio n (%) 0.33 0.33 3.21 0.35 0.35 0.20 0.31

Comments : In order to avoid singularities near the prescribed displacements, results have been obtained with a 16m beam and a measure of the results done at section x=8m. It implied the modification of the Reference values using the formulas given in the validation guide.


no. 50

STRUCTURAL MECHANICS EVALUATION FORM Software: SolidWorks Simulation Version: 2010 PR1 Computer configuration used: Dell Precision T5500, Windows Vista x64 SP2, Intel Xeon quad core, 16Gb RAM, graphics card NVIDIA Quadro FX 1800. Test name: RECTANGULAR SECTION SHAPE BEAM UNDER TORSION Codification: SSLV 06-89

Test performed by : Julien BOISSAT Date: 09/10/2009 Model used Finite elements  Boundary elements  Other  Element type : TETRA 10 Number of degrees of freedom or mesh density : L = 10 m L = 20 m Nb of nodes = 11952 Nb of nodes = 51366 Nb of elements = 7517 Nb of elements = 33789 Nb of DOF = 35397 Nb of DOF = 153405 Results : Calculated Location Physical quantity Reference value value

Deviatio n (%)

Points A and B, middle of the long sides

L = 10 m

θ /L (rd/m) σ xy | max (MPa)

2.78 × 10-3 203.7(1)

2.73 × 10-3 202.7

1.8 0.5

L = 20 m

θ /L (rd/m) σ xy | max (MPa)

2.78 × 10-3 203.7(1)

2.79 × 10-3 203.3

0.36 0.15

Comments : (1) The calculated σ xy | max stress is the value found on the lines of the long sides when far enough from the extremities in order to avoid the singularities. The "Roark’s Formulas for Stress & Strain" (6th ed. p.348) gives the following formula for a rectangular beam with a “2a × 2b” section (a ≥ b) : 2 3 4 3T ⎡ b b ⎞ b ⎞ b ⎞ ⎤ ⎛ ⎛ ⎛ Max τ = ⎢1 + 0.6095 + 0.8865⎜ ⎟ − 1.8023 ⎜ ⎟ + 0.9100 ⎜ ⎟ ⎥ which gives the 8ab ² ⎢⎣ a ⎝ a ⎠ ⎝ a ⎠ ⎝ a ⎠ ⎥⎦

reference value of 203.7 MPa. This value was used in place of the one prescribed by the validation guide which used one taken from an abacus (less accurate).


no. 51

STRUCTURAL MECHANICS EVALUATION FORM Software: SolidWorks Simulation Version: 2010 PR1 Computer configuration used: Dell Precision T5500, Windows Vista x64 SP2, Intel Xeon quad core, 16Gb RAM, graphics card NVIDIA Quadro FX 1800. Test name: BLOCK STRETCHED UNDER ITS OWN WEIGHT Codification: SSLV 07-89 D A

E

C

B

Test performed by : Julien BOISSAT Date: 09/10/2009 Model used Finite elements  Boundary elements  Other  Element type : TETRA 10 Number of degrees of freedom or mesh density : Nb of nodes = 9810 Nb of elements = 6380 Nb of DOF = 29427 Results : Calculated Location Physical quantity Reference value value Point B Point B and C Point A and D Point A Point E

w B (m) Δw (m) Δu (m) σ zz (MPa) σ zz (MPa)

1.72 × 10 -6 0.014 × 10 -6 0.17 × 10 -6 0.229 0.1145

1.72 × 10 -6 0.014 × 10 -6 0.17 × 10 -6 0.229 0.1148

Deviati on (%)

0 0 0 0 0.26

Comments :


no. 52

STRUCTURAL MECHANICS EVALUATION FORM Software: SolidWorks Simulation Version: 2010 PR1 Computer configuration used: Dell Precision T5500, Windows Vista x64 SP2, Intel Xeon quad core, 16Gb RAM, graphics card NVIDIA Quadro FX 1800. Test name: PRISMATIC BEAM UNDER PURE BENDING Codification: SSLV 08-89 B

E

A

C F Test performed by : Julien BOISSAT Date: 09/10/2009 Model used Finite elements  Boundary elements  Other  Element type : TETRA 10 Number of degrees of freedom or mesh density : Nb of nodes = 9455 Nb of elements = 5972 Nb of DOF = 28893 Results : Location

Physical quantity

Reference value

Point B(1) Point A Point B Point F or G Point D or E

σ zz (MPa) u A (m) w B (m) v F = -vG (m) v D = -v E (m)

10 -4 × 10-4 2 × 10 -4 0.15 × 10 -4 -0.15 × 10-4

Calculated value 10 -4 × 10-4 2 × 10 -4 0.15 × 10 -4 -0.15 × 10-4

Deviatio n (%) 0 0 0 0 0

Comments : (1) Supposed typographic error in the validation guide: it should read "Point B" instead of "Point A" on this location to calculate σ zz (MPa).


no. 53

STRUCTURAL MECHANICS EVALUATION FORM Software: SolidWorks Simulation Version: 2010 PR1 Computer configuration used: Dell Precision T5500, Windows Vista x64 SP2, Intel Xeon quad core, 16Gb RAM, graphics card NVIDIA Quadro FX 1800. Test name: THICK PLATE WITH ITS EDGES FIXED Codification: SSLV 09-89

C Test performed by : Julien BOISSAT Date: 09/10/2009 Model used Finite elements  Boundary elements  Other  Element type : TETRA 10 Number of degrees of freedom or mesh density : In both cases, meshing and calculating were done with the default parameters. Results :

Load : Pressure p = 1 MPa Location

λ = 10

λ = 20

λ = 50

λ = 75

λ = 100

H20 Q4 Ana. H20 Q4 Ana. H20 Q4 Ana. H20 Q4 Ana. H20 Q4 Ana.

Physical quantity

wC (m)


Reference value 0.76231 × 10 -4 0.78661 × 10 -4 0.6552 × 10 -4 0.53833 × 10 -3 0.55574 × 10 -3 0.52416 × 10 -3 0.80286 × 10 -2 0.8348 × 10 -2 0.81900 × 10 -2 0.26861 × 10 -1 0.28053 × 10 -1 0.27641 × 10 -1 0.63389 × 10 -1 0.66390 × 10 -1 0.65520 × 10 -1

Calculated value

0.7740 × 10

-4

0.5485 × 10 -3

0.8234 × 10 -2

0.2766 × 10 -1

0.65633 × 10 -1

Deviation (%)

1.53 1.60 18.13 1.89 1.30 4.64 2.56 1.37 0.54 2.97 1.40 0.07 3.54 1.14 0.17

no. 54


6

Load : Concentrated force F = 1 × 10 N Location

λ = 10

λ = 20

λ = 50

λ = 75

λ = 100

H20 Q4 Ana. H20 Q4 Ana. H20 Q4 Ana. H20 Q4 Ana. H20 Q4 Ana.

Physical quantity

wC (m)

Reference value 0.42995 × 10 -3 0.41087 × 10 -3 0.29146 × 10 -3 0.25352 × 10 -2 0.25946 × 10 -2 0.23317 × 10 -2 0.35738 × 10 -1 0.37454 × 10 -1 0.36433 × 10 -1 0.11837 0.12525 0.12296 0.27794 0.29579 0.29146

Calculated value(1)

0.41923 × 10

Deviation (%) -3

0.25932 × 10 -2

0.36962 × 10 -1

0.12326

0.29077

2.49 2.03 43.84 2.29 0.05 11.21 3.42 1.31 1.45 4.12 1.60 0.24 4.62 1.70 0.24

Comments : (1) The values in the above table are the average of the calculated values on the vertical edge (thickness) going through Point C because a concentrated force creates a singularity. The test is clearly a success : it shows plainly the growing deviation between a calculated displacement with a “thin PLATE type” analytical solution and the displacement calculated with the SolidWorks Simulation 3D model when the slenderness ratio decreases.


no. 55


2. Non linear static EVALUATION FORM Software: SolidWorks Simulation Version: 2010 PR1 Computer configuration used: Dell Precision T5500, Windows Vista x64 SP2, Intel Xeon quad core, 16Gb RAM, graphics card NVIDIA Quadro FX 1800. Test name: RECTANGLE UNDER PURE BENDING (PLANE STRESS, PERFECT PLASTICITY) Codification: SSNP 11-89

Test performed by : Julien BOISSAT Date: 12/10/2009 Model used Finite elements  Boundary elements  Other  Element type :SHELL Number of degrees of freedom or mesh density : Nb of nodes = 100 Nb of elements = 144 Nb of DOF = 600 Results : u A (mm)

0.02875 0.05 0.1 0.15 0.2 0.3 0.4 0.5 ↓

∞

Value type

Reference value

Calculated value

Deviation (%)

σ O xx (MPa) M O (N.m) M M M M M M M σ L xx M L

483.0 805.0 1074 1174 1193 1199 1204 1205 1206 483 1207.5

502.0 789 1060 1163 1182 1187 1193 1194 1194 - (1) -

3.93 -1.95 -1.32 -0.93 -0.92 -1.03 -0.88 -0.92 -1.00 -

Comments : (1) The software cannot create an infinite displacement. Moreover, in order to obtain convergence, a non-zero tangent modulus was used.


no. 56

STRUCTURAL MECHANICS EVALUATION FORM Software: SolidWorks Simulation Version: 2010 PR1 Computer configuration used: Dell Precision T5500, Windows Vista x64 SP2, Intel Xeon quad core, 16Gb RAM, graphics card NVIDIA Quadro FX 1800. Test name: CYLINDER UNDER PRESSURE (PLANE STRAIN, PERFECT ELASTOPLASTICITY) Codification: SSNP 13-89

Test performed by : Julien BOISSAT Date: 12/10/2009 Model used Finite elements  Boundary elements  Other  Element type :SHELL Number of degrees of freedom or mesh density : Nb of nodes = 1198 Nb of elements = 2246 Nb of DOF = 7188 Results : Pressure p (MPa)

Radius r (mm)

100 (elasticity)

1 1.5 2 1 1.5 2

Physical quantity (MPa)

Starts yielding Complete yield


Reference value

Calculated value

Deviation (%)

-100 -25.93 0 166.7 92.59 66.7

-97.40 -27.46 0.16 176.32 97.48 71.99

2.60 5.90 5.77 5.02 7.93

p y

129.68

129.35

0.25

plim

240.11

231

3.8

σ r

σ θ

no. 57


Fig1: Tube starts yielding on inner face

Fig2: Tube finishes yielding on outer face

Comments :


no. 58


3. Linear dynamic EVALUATION FORM Software: SolidWorks Simulation Version: 2010 PR1 Computer configuration used: Dell Precision T5500, Windows Vista x64 SP2, Intel Xeon quad core, 16Gb RAM, graphics card NVIDIA Quadro FX 1800. Test name: THIN CYLINDER FIXED ON BOTH ENDS Codification: SDLA 01-89

Test performed by : Julien BOISSAT Date: 19/10/2009 Model used Finite elements  Boundary elements  Other  Element type : SHELL 6 Number of degrees of freedom or mesh density : Nb of nodes = 4464 Nb of elements = 2190 Nb of DOF = 25776 Results : Reference values Frequency (Hz)

m=1

2

3

E C S E C S E C S

n=2

4

6

8

10

12

14

1925.5 2772 3929.0 5251 5892.7 6997

700 771.1 880 1620 1775.8 2088 2968.0 3441

525 538.5 568 980 1041.5 1121 1650 1764.9 1915

720 719.6 742 900 922.3 952 1350 1323.4 1368

1095 1081.8 1104 1140 1165.6 1189 1325 1361.3 1383

1559 1549.7 1573 1595.4 1620 1711 1698.7 1720

2118 2108.5 2132 2140.9 2167 2225 2207.5 2233

8

10

12

14

717.4 0.31 910.5 1.30 1292.1 2.41

1079.4 0.22 1157 0.74 1336.7 1.84

1545 0.30 1586.5 0.57 1677.2 1.28

2099.1 0.45 2127.4 0.63 2185.2 1.02

Calculated values (Hz) Result m = 1 Deviation(%) Result 2 Deviation(%) Result 3 Deviation(%)

n=2

1921.8 0.19 3914.3 0.38 5858.8 0.58

4

6

766.3 534.7 0.63 0.71 1760.5 1025.9 0.87 1.50 2934 1730 1.16 2.00


no. 59


m = 1, n = 6

m = 2, n = 6

m = 3, n = 6

Comments : The deviation was calculated checking the results of SolidWorks Simulation against the results « average of the 2 codes » (marked as “C” in the table).


no. 60

STRUCTURAL MECHANICS EVALUATION FORM Software: SolidWorks Simulation Version: 2010 PR1 Computer configuration used: Dell Precision T5500, Windows Vista x64 SP2, Intel Xeon quad core, 16Gb RAM, graphics card NVIDIA Quadro FX 1800. Test name: SLENDER FOLDED BEAM, ONE END FIXED THE OTHER FREE Codification: SDLL 02-89

Test performed by : Julien BOISSAT Date: 19/10/2009 Model used Finite elements  Boundary elements  Other  Element type : BEAM Number of degrees of freedom or mesh density : Nb of nodes = 161 Nb of elements = 150 Nb of DOF = 900 Results : Nature of the Frequency (Hertz) vibration mode Deviation (%) Order Reference value Calculated value i 1 2 3 4

1,2 3,4 5,6 7,8

11.76 105.88 294.10 576.44

11.75 105.8 293.5 575.1

0.08 0.07 0.20 0.23

Order 2

Order 4

Comments : The model was made with an arbitrary angle of 3° for the fold as it wasn’t specified in the test description.


no. 61

STRUCTURAL MECHANICS EVALUATION FORM Software: SolidWorks Simulation Version: 2010 PR1 Computer configuration used: Dell Precision T5500, Windows Vista x64 SP2, Intel Xeon quad core, 16Gb RAM, graphics card NVIDIA Quadro FX 1800. Test name: SLENDER BEAM ON TWO SIMPLE SUPPORTS UNDER AXIAL FORCE Codification: SDLL 05-89

Test performed by : Julien BOISSAT Date: 19/10/2009 Model used Finite elements  Boundary elements  Other  Element type : BEAM Number of degrees of freedom or mesh density : Nb of nodes = 119 Nb of elements = 117 Nb of DOF = 705 Results : Nature of the vibration mode

|F x| = 0 |F x| = 105 N

Bending 1 Bending 2 Bending 1 Bending 2

Frequency (Hertz) Reference

Calculated

28.702 114.807 22.434 109.080

28.702 114.807 22.434 109.08

Deviation (%)

0 0 0 0

|F x| = 0 N, Bending 1

|F x| = 105 N, Bending 2 Comments :


no. 62

STRUCTURAL MECHANICS EVALUATION FORM Software: SolidWorks Simulation Version: 2010 PR1 Computer configuration used: Dell Precision T5500, Windows Vista x64 SP2, Intel Xeon quad core, 16Gb RAM, graphics card NVIDIA Quadro FX 1800. Test name: PLANAR FRAME MADE OF I BEAMS Codification: SDLL 08-89 B G

E Test performed by : Julien BOISSAT Date: 19/10/2009 Model used Finite elements  Boundary elements  Other  Element type : SHELL Number of degrees of freedom or mesh density : Nb of nodes = 5473 Nb of elements = 2524 Nb of DOF = 63486 Results : Order of Vibration mode Frequency (Hertz) Deviation (%) the w B / wG vibration Reference Calculated Reference Calculated Frequency w B / wG mode 1 16.456 16.466 1.213 1.16 0.08 4.35 2 38.165 37.158 -0.412 -0.422 2.64 2.54

Mode 1 Dynamic response : Point

B, E G G

Value type (m)

w B max wG max w B + wG max

Values Reference

Calculated

-2

-1.02 × 10 -1 -12.4 × 10 -2 -2.26 × 10 -1

-9.8 × 10 -12.5 × 10 -2 -2.27 × 10 -1

Deviation (%)

3.92 0.81 0.44

Comments :


no. 63

STRUCTURAL MECHANICS EVALUATION FORM Software: SolidWorks Simulation Version: 2010 PR1 Computer configuration used: Dell Precision T5500, Windows Vista x64 SP2, Intel Xeon quad core, 16Gb RAM, graphics card NVIDIA Quadro FX 1800. Test name: SLENDER BEAM WITH VARIABLE RECTANGULAR SECTION, ONE END FIXED THE OTHER FREE Codification: SDLL 09-89

Test performed by : Julien BOISSAT Date: 19/10/2009 Model used Finite elements  Boundary elements  Other  Element type : TETRA10 Number of degrees of freedom or mesh density : β = 4 Nb of nodes = 11686 Nb of elements = 6691 Nb of DOF = 34743 Results : Nature of the vibration mode 1 2 Bending 3 4 5

β = 5 Nb of nodes = 13362 Nb of elements = 7980 Nb of DOF = 39717

Frequency (Hertz) β = 4

Frequency (Hertz) β = 5

Deviation (%)

Reference

Calculated

Reference

Calculated

β = 4

β = 5

54.18 171.94 384.40 697.24 1112.28

54.19 171.56 381.97 688.61 1090.1

56.55 175.79 389.01 702.36 1117.63

56.54 175.44 386.67 693.16 1095.2

-0.02 0.22 0.64 1.25 2.03

0 0.20 0.59 1.32 2.02

Mode 3

Mode 4 Comments :


no. 64

STRUCTURAL MECHANICS EVALUATION FORM Software: SolidWorks Simulation Version: 2010 PR1 Computer configuration used: Dell Precision T5500, Windows Vista x64 SP2, Intel Xeon quad core, 16Gb RAM, graphics card NVIDIA Quadro FX 1800. Test name: SLENDER BEAM WITH VARIABLE RECTANGULAR SECTION, BOTH ENDS FIXED Codification: SDLL 10-89

Test performed by : Julien BOISSAT Date: 19/10/2009 Model used Finite elements  Boundary elements  Other  Element type : TETRA10 Number of degrees of freedom or mesh density : Nb of nodes = 15046 Nb of elements = 8760 Nb of DOF = 44802 Results : Order of the vibration mode

Frequency of reference (Hz)

Frequency Calculated (Hz)

Deviation (%)

1 2 3 4

143.303 396.821 779.425 1289.577

146.09 399.69 779.4 1281.9

1.94 0.72 0.01 0.60

Mode 1

Mode 2


no. 65


Mode 3

Mode 4

Order of the vibration mode Reference 1 Calculation Deviation(%) Reference 2 Calculation Deviation(%) Reference 3 Calculation Deviation(%) Reference 4 Calculation Deviation(%)

x = 0. 0 0 0 0 0 0 0 0 -

0.1 0.237 0.237 0 -0.504 -0.504 0 0.670 0.670 0 -0.670 -0.674 0.6

Vibration mode φi (x) 0.2 0.3 0.4 0.703 1 0.859 0.703 1 0.861 0 0 0.23 -0.818 0 1 -0.822 0.06 1 0.49 0 0.210 -0.831 0.257 0.223 -0.830 0.266 6.19 0.12 3.5 0.486 0 -0.594 0.49 0.09 -0.602 0.82 1.35

0.5 0.354 0.357 0.85 0.752 0.756 0.53 1 1 0 1 1 0

0.6 0 0 0 0 0 0 0 0 -

Comments :


no. 66

STRUCTURAL MECHANICS EVALUATION FORM Software: SolidWorks Simulation Version: 2010 SP0 Computer configuration used: Dell Precision T5500, Windows Vista x64 SP2, Intel Xeon quad core, 16Gb RAM, graphics card NVIDIA Quadro FX 1800. Test name: THIN CIRCULAR RING COMPLETELY FREE Codification: SDLL 11-89

Test performed by : Julien BOISSAT Model used Finite elements  Boundary elements  Element type : TETRA10 and BEAM Number of degrees of freedom or mesh density : Solid elements: Nb of nodes = 13955 Nb of elements = 7401 Nb of DOF = 41865 Results : Nature of the vibration mode

Date: 27/10/2009 Other 

Beam elements Nb of nodes = 400 Nb of elements = 200 Nb of DOF = 1200 Frequency (Hz)

i

Order

Reference value

value Beam

Solid Beam

0,1 2 3 4 5

1,2,3 4,5 6,7 8,9 10,11

0. 318.38 900.46 1726.55 2792.21

0 319.22 902.84 1731.1 2799.5

0.12 0.31 0.58 0.93

i=1


Calculated Solid In the plane 0 317.99 897.7 1716.59 2766.41

Deviation (%)

0.26 0.26 0.26 0.26

i=2

no. 67


i=3

i=4

i=5 Nature of the vibration mode

Frequency (Hz)

i

Order

Reference value

0,1 2 3 4

1,2,3 4,5 6,7 8,9

0 511 1590 3184

Calculated value Solid Beam Transverse 0 0 510 511 1572 1594 3116 3202

Deviation (%) Solid

Beam

0.20 1.15 2.18

0 0.25 0.57

i=0

i=1

i=2

i=3

i=4 Comments :


no. 68

STRUCTURAL MECHANICS EVALUATION FORM Software: SolidWorks Simulation Version: 2010 SP0 Computer configuration used: Dell Precision T5500, Windows Vista x64 SP2, Intel Xeon quad core, 16Gb RAM, graphics card NVIDIA Quadro FX 1800. Test name: THIN CIRCULAR RING FIXED AT TWO POINTS Codification: SDLL 12-89 Test performed by : Julien BOISSAT Date: 27/10/2009 Model used Finite elements  Boundary elements  Other  Element type : TETRA10 and BEAM Number of degrees of freedom or mesh density : Solid elements Beam elements Nb of nodes = 14367 Nb of nodes = 418 Nb of elements = 7661 Nb of elements = 209 Nb of DOF = 43371 Nb of DOF = 1242 Results : Order of the Frequency (Hz) vibration mode Deviation (%) Calculated value Reference value j i Solid Beam Solid Beam 1 anti 1 235.3 235.6 235.9 0.13 0.25 2 sym 1 575.3 574.5 576.6 0.14 0.23 3 anti 2 1105.7 1101.5 1108 0.38 0.21 4 anti 3 1405.6 1400.9 1407.9 0.33 0.16 5 sym 2 1751.1 1737.4 1752.2 0.78 0.06 6 anti 4 2557.0 2529.2 2558.3 1.09 0.05 7 sym 3 2801.5 2726.5 2759.4 2.68 1.50 Antisymmetric modes

Mode 1


Symmetric modes

Mode 2

no. 69

STRUCTURAL MECHANICS Mode 6

Mode 7

Mode 3

Mode 5

Mode 4

Comments :


no. 70

STRUCTURAL MECHANICS EVALUATION FORM Software: SolidWorks Simulation Version: 2010 SP0 Computer configuration used: Dell Precision T5500, Windows Vista x64 SP2, Intel Xeon quad core, 16Gb RAM, graphics card NVIDIA Quadro FX 1800. Test name: THIN CIRCULAR RING FIXED BY AN ELASTIC LEG Codification: SDLL 13-89

Test performed by : Julien BOISSAT Date: 27/10/2009 Model used Finite elements  Boundary elements  Other  Element type : TETRA10 Number of degrees of freedom or mesh density : Nb of nodes = 15107 Nb of elements = 8140 Nb of DOF = 45240 Results : Frequency (Hz)

Nature of the vibration mode

Reference value

Calculated value

1 anti 2 sym 3 anti 4 anti 5 sym 6 anti

28.8 189.3 268.8 641. 682. 1063.

30.0 189.7 268.7 659.7 681.8 1100.5


Deviation (%)

4.00 0.21 0.04 2.89 0.03 3.41

no. 71


Mode 2 Mode 1

Mode 4 Mode 3

Mode 5

Mode 6

Comments :


no. 72

STRUCTURAL MECHANICS EVALUATION FORM Software: SolidWorks Simulation Version: 2010 SP0 Computer configuration used: Dell Precision T5500, Windows Vista x64 SP2, Intel Xeon quad core, 16Gb RAM, graphics card NVIDIA Quadro FX 1800. Test name: VIBRATION MODES OF AN ELBOWED PIPE Codification: SDLL 14-89

Test performed by : Julien BOISSAT Date: 10/11/2009 Model used Finite elements  Boundary elements  Other  Element type : BEAMS Number of degrees of freedom or mesh density : l=0m l = 0.6 m l = 2 m Nb of nodes = 561 Nb of nodes = 659 Nb of nodes = 829 Nb of elements = 280 Nb of elements = 416 Nb of elements = 646 Nb of DOF = 1674 Nb of DOF = 2490 Nb of DOF = 3870 Results : Nature of the vibration mode

l=0m

l = 0.6 m

l=2m

Frequency (Hz) Reference

Calculated

Deviation (%)

44.23 119 125 227 33.4 94 100 180 17.9 24.8 25.3 27

44.15 119.59 126.02 226.37 33.22 94.12 98.9 182.95 17.65 24.43 24.95 26.73

0.18 0.50 0.82 0.28 0.54 0.13 1.10 1.64 1.40 1.49 1.38 1.00

Transverse 1 In plane 1 Transverse 2 In plane 2 Transverse 1 In plane 1 Transverse 2 In plane 2 Transverse 1 In plane 1 Transverse 2 In plane 2


no. 73

STRUCTURAL MECHANICS Modes for l = 2 m

In the plane

Transverse

Mode 1

Mode 1

Mode 2

Mode 2

Comments :


no. 74

STRUCTURAL MECHANICS EVALUATION FORM Software: SolidWorks Simulation Version: 2010 SP0 Computer configuration used: Dell Precision T5500, Windows Vista x64 SP2, Intel Xeon quad core, 16Gb RAM, graphics card NVIDIA Quadro FX 1800. Test name: THIN FREE RING WITH A PUNCTUAL MASS Codification: SDLL 16-89

Test performed by : Julien BOISSAT Date: 28/10/2009 Model used Finite elements  Boundary elements  Other  Element type : TETRA 10 Number of degrees of freedom or mesh density : Nb of nodes = 13896 Nb of elements = 7360 Nb of DOF = 41829 Results : Order of the vibration mode

Frequency (Hz) Reference

Calculated

Deviation (%)

In plane 1,2,3 Sym 4 Anti 5 Sym 6 Anti 7 1,2,3 4 5

0. 227.29 297.87 718.42 873.88 Transverse 0. 409.8 510.2


0 227.7 296.33 717.28 860.16

0.05 0.52 0.16 1.60

0 409.22 508.21

0.15 0.38

no. 75


Vibration modes in plane

Mode 4

Mode 5

Mode 6

Mode 7 Transverse vibration modes

Mode 4

Mode 5

Comments :


no. 76

STRUCTURAL MECHANICS EVALUATION FORM Software: SolidWorks Simulation Version: 2010 SP0 Computer configuration used: Dell Precision T5500, Windows Vista x64 SP2, Intel Xeon quad core, 16Gb RAM, graphics card NVIDIA Quadro FX 1800. Test name: THIN SQUARE PLATE WITH 3 OR 4 FREE EDGES Codification: SDLS 01-89

Test performed by : Julien BOISSAT Date: 28/10/2009 Model used Finite elements  Boundary elements  Other  Element type : SHELL 6 Number of degrees of freedom or mesh density : 1.Fixed edge 2.Free Nb of nodes = 4629 Nb of nodes = 4629 Nb of elements = 2246 Nb of elements = 2246 Nb of DOF = 27360 Nb of DOF = 27774 Results : 1.Fixed edge Order of the Frequency (Hertz) vibration mode Deviation (%) Reference value Calculated value i 1 8.7266 8.6733 0.61 2 21.3042 21.252 0.25 3 53.5542 53.16 0.74 4 68.2984 67.914 0.57 5 77.7448 77.312 0.56 6 136.0471 135.27 0.57

Mode 1

Mode 2

Mode 3

Mode 4


no. 77


Mode 6

Mode 5 2.Free Order of the vibration mode i 7 8 9 10 11

Frequency (Hertz) Reference value

Calculated value

33.7119 49.4558 61.0513 87.5160 87.5160

33.645 48.922 60.604 86.864 86.864

Mode 7

Mode 10

Mode 8

Deviation (%)

0.20 1.09 0.74 0.75 0.75

Mode 9

Mode 11

Comments :


no. 78

STRUCTURAL MECHANICS EVALUATION FORM Software: SolidWorks Simulation Version: 2010 SP0 Computer configuration used: Dell Precision Prec ision T5500, Windows Vista x64 SP2, Intel Xeon quad core, 16Gb RAM, graphics card car d NVIDIA Quadro FX 1800. Test name: THIN RHOMBOID PLATE FIXED ON ONE EDGE Codification: SDLS 02-89

Test performed by : Julien BOISSAT Date: 28/10/2009 Model used Finite elements  Boundary elements  Other  Element type : SHELL 6 Number of degrees of freedom or mesh density : α = 0° α = 15° Nb of nodes = 6561 Nb of nodes = 6381 Nb of elements = 3200 Nb of elements = 3110 Nb of DOF = 38880 Nb of DOF = 37800 α = 30° α = 45° Nb of nodes = 5701 Nb of nodes = 4737 Nb of elements = 2770 Nb of elements = 2288 Nb of DOF = 33720 Nb of DOF = 27936 Results : Nature of the Frequency (Hertz) vibration mode Deviation (%) α α = 0° α = 15° α = 30° α = 45°

i 1 2 1 2 1 2 1 2

Reference value

Calculated value

8.7266 8.6734 21.3042 21.253 8.9990 8,9538 22.1714 21,728 9.8987 9.816 25.4651 23.513 11.15 11.264 27 28.103 Vibration modes α = 45°

f 1=11.26 Hz

0.61 0.24 2.04 0.84 0.84 8.30 -1.01 -3.91

f 2=28.1 Hz

Comments :


no. 79

STRUCTURAL MECHANICS EVALUATION FORM Software: SolidWorks Simulation Version: 2010 SP0 Computer configuration used: Dell Precision Prec ision T5500, Windows Vista x64 SP2, Intel Xeon quad core, 16Gb RAM, graphics card car d NVIDIA Quadro FX 1800. Test name: THIN RECTANGULAR PLATE SIMPLY SUPPORTED ON EDGES Codification: SDLS 03-89

Test performed by : Julien BOISSAT Model used Finite elements  Boundary elements  Element type : SHELL 6 Number of degrees of freedom or mesh density : Nb of nodes = 4491 Nb of elements = 2176 Nb of DOF = 26940

Date: 28/10/2009 Other 

Results : Nature of the vibration mode

Frequency (Hertz)

i

j

Reference value

Calculated value

1 2 1 3 2 3

1 1 2 1 2 2

35.63 68.51 109.62 123.32 142.51 197.32

35.62 68.49 109.58 123.25 142.41 197.11


Deviation (%)

0.03 0.03 0.04 0.06 0.07 0.11

no. 80


1,1

1,2

2,2

2,1

3,1

3,2

Comments :


no. 81

STRUCTURAL MECHANICS EVALUATION FORM Software: SolidWorks Simulation Version: 2010 SP0 Computer configuration used: Dell Precision Prec ision T5500, Windows Vista x64 SP2, Intel Xeon quad core, 16Gb RAM, graphics card car d NVIDIA Quadro FX 1800. Test name: THIN RING SHAPED PLATE FIXED ON I NNER EDGE Codification: SDLS 04-89


Date: 28/10/2009 Other 

Results : Nature of the vibration mode

Frequency (Hertz)

i

j

Reference value

Calculated value

0 0 1 1 2 2 3 3

0 1 0 1 0 1 0 1

79.26 518.85 81.09 528.61 89.63 559.09 112.79 609.70

79.34 516.37 80.95 526.68 89.56 556.98 113.04 607.96


Deviation (%)

0.10 0.48 0.17 0.37 0.08 0.38 0.22 0.29

no. 82


0,0

0,1

1,0

1,1

2,0

2,1

3,1 3,0 Comments :


no. 83

STRUCTURAL MECHANICS EVALUATION FORM Software: SolidWorks Simulation Version: 2010 SP0 Computer configuration used: Dell Precision T5500, Windows Vista x64 SP2, Intel Xeon quad core, 16Gb RAM, graphics card NVIDIA Quadro FX 1800. Test name: COMPRESSOR BLADE: THIN SHELL FIXED-FREE Codification: SDLS 05-89


Date: 28/10/2009 Other 

Results : Frequency (Hertz)

Nature of the vibration mode

Reference value

Calculated value

1 2 3 4 5 6

85.6 134.5 259.0 351.0 395.0 531.0

85.9 138.4 246.9 342.4 386.4 528.2


Deviation (%)

0.35 2.82 4.90 2.51 2.23 0.53

no. 84


Mode 1

Mode 2

Mode 4 Mode 3

Mode 5

Mode 6

Comments :


no. 85

STRUCTURAL MECHANICS EVALUATION FORM Software: SolidWorks Simulation Version: 2010 SP0 Computer configuration used: Dell Precision T5500, Windows Vista x64 SP2, Intel Xeon quad core, 16Gb RAM, graphics card NVIDIA Quadro FX 1800. Test name: THIN WINGED CIRCULAR PLATE Codification: SDLS 06-89


Date: 28/10/2009 Other 

Results : Nature of the vibration mode Torsion Bending

ND 0 1 2 3 4 4

β (°) 0 45 90 135 180 180 135 90 45 0

Frequency (Hertz) Reference value Calculated value

D1

D2

D1

D2

267.2 264.7 295.1 361.1 -390.5 -----

902 901 971 1210 1663 1643 2189 2627 2783 2805

280.49 279.8 304.8 365.09

948.92 954.76 1017.3 1242.5 1679.4 1670.8 2215.4 2681.9 2902.7 2932.6

393.92

Deviation (%)

4.74 5.40 3.18 1.09 0.87

4.94 5.63 4.55 2.62 0.98 1.66 1.19 2.05 4.12 4.35

D1 Family


no. 86


f = 280.49 Hz

f = 279.8 Hz

f = 365.09 Hz

f = 304.8 Hz

f = 393.92 Hz

D2 Family

f = 948.92 Hz

f = 954.76 Hz

f = 1017.3 Hz

f = 1242.5 Hz

f = 1679.4 Hz

f = 1670.8 Hz

f = 2215.4 Hz

f = 2681.9 Hz

f = 2902.7 Hz

f = 2932.6 Hz Comments :


no. 87

STRUCTURAL MECHANICS EVALUATION FORM Software: SolidWorks Simulation Version: 2010 SP0 Computer configuration used: Dell Precision T5500, Windows Vista x64 SP2, Intel Xeon quad core, 16Gb RAM, graphics card NVIDIA Quadro FX 1800. Test name: THIN SPHERE COMPLETELY IMMERSED IN A PERFECT AND INCOMPRESSIBLE FLUID Codification: SDLS 07-89

Test performed by : Julien BOISSAT Date: 28/10/2009 Model used Finite elements  Boundary elements  Other  Element type : SHELL 6 Number of degrees of freedom or mesh density : In the void t/R = 0.04 t/R = 0.004 Nb of nodes = 4242 Nb of nodes = 10130 Nb of elements = 2120 Nb of elements = 5064 Nb of DOF = 25452 Nb of DOF = 60780 Results : In vacuum Frequency (Hertz) Nature of the vibration Reference value Calculated value Deviation (%) mode t/R = 0.04 t/R = 0.004 t/R = 0.04 t/R = 0.004 i j 2 0 237.25 236.71 237.41 236.93 0.07 0.09 3 0 282.85 280.49 283.15 280.66 0.11 0.02 4 0 305.24 297.65 305.39 297.8 0.05 0.05 5 0 324.17 306.16 324.16 306.44 0 0.09 6 0 346.76 311.10 346.52 311.41 0.07 0.1 7 0 376.68 314.35 376.55 314.71 0.03 0.11 8 0 416.0 316.77 415.17 317.28 0.20 0.16 9 0 465.75 318.80 463.85 319.26 0.41 0.14 10 0 526.20 320.71 522.84 321.42 0.64 0.22


no. 88


i = 2

i = 3

i = 4 Comments : The simulation of the immersed sphere is out of the software’s range.


no. 89

STRUCTURAL MECHANICS EVALUATION FORM Software: SolidWorks Simulation Version: 2010 SP0 Computer configuration used: Dell Precision T5500, Windows Vista x64 SP2, Intel Xeon quad core, 16Gb RAM, graphics card NVIDIA Quadro FX 1800. Test name: BENDING OF SYMMETRICAL FRAME Codification: SDLX 01-89

Test performed by : Julien BOISSAT Date: 28/10/2009 Model used Finite elements  Boundary elements  Other  Element type : BEAM Number of degrees of freedom or mesh density : Nb of nodes = 389 Nb of elements = 385 Nb of DOF = 2292 Results : Nature of the vibration mode i 1 anti 2 anti 3 sym 4 sym 5 anti 6 sym 7 anti 8 sym 9 anti 10 anti 11 sym 12 anti 13 sym

Frequency (Hertz) Reference value

Calculated value

8.8 29.4 43.8 56.3 96.2 102.6 147.1 174.8 178.8 206 266.4 320 335

8.8 29.4 43.9 56.6 96.2 103 147.2 175.2 179.5 207.3 266.7 320.8 336.1


Deviation (%)

0 0 0.22 0.53 0 0.39 0.06 0.23 0.34 0.63 0.11 0.25 0.33

no. 90


Mode 2

Mode 8 Comments :


Mode 5

Mode 13

no. 91

STRUCTURAL MECHANICS EVALUATION FORM Software: SolidWorks Simulation Version: 2010 SP0 Computer configuration used: Dell Precision T5500, Windows Vista x64 SP2, Intel Xeon quad core, 16Gb RAM, graphics card NVIDIA Quadro FX 1800. Test name: ASSEMBLY OF THIN RECTANGULAR SHAPED SHEETS Codification: SDLX 03-89

Test performed by : Julien BOISSAT Date: 28/10/2009 Model used Finite elements  Boundary elements  Other  Element type : SHELL 6 Number of degrees of freedom or mesh density : Nb of nodes = 4600 Nb of elements = 2260 Nb of DOF = 27600 Results : Frequency (Hertz)

Nature of the vibration mode i

Experimental

1 2 3 4 5 6

606 760 865 944 1113 1144


Finite elements model 584 ± 1% 826 ± 1.5% 855 ± 1.7% 911 ± 2% 1113 ± 3.6% 1136 ± 4%

Calculated value 585 826 852 912 1107 1157

Deviation (%)

3.59 7.99 1.53 3.51 0.54 1.12

0.17 0 0.35 0.11 0.54 1.82

no. 92


Mode 1

Mode 3

Mode 5

Mode 2

Mode 4

Mode 6

Comments :


no. 93

II.


THERMAL

no. 94

THERMAL

1. Linear steady state thermal EVALUATION FORM Software: SolidWorks Simulation Version: 2010 SP0 Computer configuration used: Dell Precision T5500, Windows Vista x64 SP2, Intel Xeon quad core, 16Gb RAM, graphics card NVIDIA Quadro FX 1800. Test name: PIPE: PRESCRIBED TEMPERATURES Codification: TPLA 01-89

Test performed by : Julien BOISSAT Date: 28/10/2009 Model used Finite elements  Boundary elements  Other  Element type : SHELL6 Number of degrees of freedom or mesh density : Nb of nodes = 1180 Nb of elements = 533 Nb of DOF = 972 Results : Reference values Calculated values r (m) T (°C) φ (W/m²) T (°C) φ (W/m²) 0.3 100 1729.91 100 1729.6 0.31 82.98 1674.11 82.98 1674.04 0.32 66.51 1621.79 66.51 1621.74 0.33 50.54 1572.64 50.54 1572.59 0.34 35.04 1526.39 35.04 1526.34 0.35 20 1482.78 20 1482.58

Deviation (%)

0 0 0 0 0 0

0 0 0 0 0 0

Reference value of the output flux Φ /l = 3260.80 W/m Calculated value Φ /l = 3260.23 W/m Deviation (%) = 0.02 Comments :


no. 95

THERMAL EVALUATION FORM Software: SolidWorks Simulation Version: 2010 SP0 Computer configuration used: Dell Precision T5500, Windows Vista x64 SP2, Intel Xeon quad core, 16Gb RAM, graphics card NVIDIA Quadro FX 1800. Test name: PIPE : PRESCRIBED TEMPERATURE, CONVECTION Codification: TPLA 02-89

Test performed by : Julien BOISSAT Date: 28/10/2009 Model used Finite elements  Boundary elements  Other  Element type : SHELL6 Number of degrees of freedom or mesh density : Nb of nodes = 1180 Nb of elements = 533 Nb of DOF = 972 Results : Reference values Calculated values r (m) T (°C) φ (W/m²) T (°C) φ (W/m²) 0.3 66.49 1005.29 66.49 1005.5 0.31 56.60 972.89 56.60 972.82 0.32 47.03 942.46 47.03 942.43 0.33 37.75 913.90 37.75 913.87 0.34 28.74 887.02 28.74 887 0.35 20 861.68 20 861.55 Reference value of the output flux Φ /l = 1894.94 W/m Calculated value Φ /l = 1893.08 W/m Deviation (%) = 0.1

Deviation (%)

0 0 0 0 0 0

0.02 0.01 0 0 0 0.02

Comments :


no. 96

THERMAL EVALUATION FORM Software: SolidWorks Simulation Version: 2010 SP0 Computer configuration used: Dell Precision T5500, Windows Vista x64 SP2, Intel Xeon quad core, 16Gb RAM, graphics card NVIDIA Quadro FX 1800. Test name: PIPE : CONVECTION Codification: TPLA 03-89

Test performed by : Julien BOISSAT Date: 28/10/2009 Model used Finite elements  Boundary elements  Other  Element type : SHELL6 Number of degrees of freedom or mesh density : Nb of nodes = 2147 Nb of elements = 1008 Nb of DOF = 2147 Results : Physical quantity T i (°C) T e (°C) φi (W/m²) φe (W/m²) Φ /l (W/m)

Reference value 272.27 205.05 34160.01 26276.93 64390.11

Calculated value 272.35 204.5 34143 26198 64358

Deviation (%) 0.03 0.27 0.05 0.30 0.05

Comments :


no. 97

THERMAL EVALUATION FORM Software: SolidWorks Simulation Version: 2010 SP0 Computer configuration used: Dell Precision T5500, Windows Vista x64 SP2, Intel Xeon quad core, 16Gb RAM, graphics card NVIDIA Quadro FX 1800. Test name: POWER OUTPUT IN A PIPE Codification: TPLA 04-89

Test performed by : Julien BOISSAT Date: 28/10/2009 Model used Finite elements  Boundary elements  Other  Element type : SHELL6 Number of degrees of freedom or mesh density : Nb of nodes = 1037 Nb of elements = 484 Nb of DOF = 939 Results : Reference value Calculated values Deviation (%) r (m) T (°C) φ (W/m²) T (°C) φ (W/m²) 1.0 20.00 -58.2 20.00 -58.12 0 0.14 1.2 28.73 -30.17 28.73 -30.12 0 0.17 1.5 32.62 2.87 32.62 2.88 0 0.35 Comments :


no. 98

THERMAL EVALUATION FORM Software: SolidWorks Simulation Version: 2010 SP0 Computer configuration used: Dell Precision T5500, Windows Vista x64 SP2, Intel Xeon quad core, 16Gb RAM, graphics card NVIDIA Quadro FX 1800. Test name: CYLINDRICAL BAR WITH FLUX DENSITY Codification: TPLA 05-89

Test performed by : Julien BOISSAT Date: 28/10/2009 Model used Finite elements  Boundary elements  Other  Element type : TETRA 10 Number of degrees of freedom or mesh density : Nb of nodes = 25557 Nb of elements = 15216 Nb of DOF = 25411 Results : z (m)

0.0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1.0

Reference value T (°C) 0.00 -4.00 4.00 24.00 56.00 100.00 156.00 224.00 304.00 396.00 500.00

Calculated value T (°C) 0.00 -4 4 24 56 100 156.0 224.0 304.0 396.0 500.0

Deviation (%)

0 0 0 0 0 0 0 0 0 0

Comments :


no. 99

THERMAL EVALUATION FORM Software: SolidWorks Simulation Version: 2010 SP0 Computer configuration used: Dell Precision T5500, Windows Vista x64 SP2, Intel Xeon quad core, 16Gb RAM, graphics card NVIDIA Quadro FX 1800. Test name: CYLINDRICAL BAR WITH CONVECTION Codification: TPLA 06-89

Test performed by : Julien BOISSAT Date: 04/11/2009 Model used Finite elements  Boundary elements  Other  Element type : TETRA 10 Number of degrees of freedom or mesh density : Nb of nodes = 25557 Nb of elements = 15216 Nb of DOF = 25411 Results : z (m)

0.0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1.0

Reference value T (°C) 0.00 0.37 0.97 2.19 4.78 10.39 22.56 48.95 106.21 230.44 500.00

Calculated value T (°C) 0.00 0.37 0.97 2.19 4.78 10.40 22.56 48.95 106.2 230.3 500.0

Deviation (%)

0 0 0 0 0.10 0 0 0.01 0.06 0

Comments :


no. 100

THERMAL EVALUATION FORM Software: SolidWorks Simulation Version: 2010 SP0 Computer configuration used: Dell Precision T5500, Windows Vista x64 SP2, Intel Xeon quad core, 16Gb RAM, graphics card NVIDIA Quadro FX 1800. Test name: ORTHOTROPIC PIPE Codification: TPLA 07-89

Test performed by : Julien BOISSAT Model used Finite elements  Boundary elements  Element type : TETRA 10 Number of degrees of freedom or mesh density : Nb of nodes = 40831 Nb of elements = 26407 Nb of DOF = 40831 Results :

z (m)

0

l/2

l

Date: 04/11/2009 Other 

r (m)

Reference value T (°C)

Calculated value T (°C)

Deviation(%)

0.030 0.035 0.040 0.045 0.050 0.030 0.035 0.040 0.045 0.050 0.030 0.035 0.040 0.045 0.050

100.01 81.90 66.22 52.38 40.00 102.51 84.40 68.72 54.88 42.51 105.01 86.90 71.22 57.38 45.01

100.8 82.95 67.33 53.39 40.74 102.6 84.44 68.76 54.92 42.54 104.4 85.93 70.18 56.43 44.33

0.79 1.28 1.68 1.93 1.85 0.09 0.05 0.06 0.07 0.07 0.58 1.12 1.46 1.66 1.51


no. 101

THERMAL

∀r, φ z (W/m²)

-500

-497

0.60

∀ z, φ Ri (W/m²)

11310

11310

0

∀ z, φ Re (W/m²)

6786

6779

0.10

Comments : In order to satisfy the boundary conditions, we split the face and applied the convection separately to each strip because the software does not currently allow ambient temperature variation for convection as a boundary condition.


no. 102

THERMAL EVALUATION FORM Software: SolidWorks Simulation Version: 2010 SP0 Computer configuration used: Dell Precision T5500, Windows Vista x64 SP2, Intel Xeon quad core, 16Gb RAM, graphics card NVIDIA Quadro FX 1800. Test name: TWO-MATERIAL PIPE : CONVECTION Codification: TPLA 08-89

Test performed by : Julien BOISSAT Date: 04/11/2009 Model used Finite elements  Boundary elements  Other  Element type : TETRA 10 Number of degrees of freedom or mesh density : Nb of nodes = 14562 Nb of elements = 9032 Nb of DOF = 14562 Results : Physical Reference value Calculated value Deviation (%) quantity T i (°C) 25.42 25.42 0 T m (°C) 17.69 17.69 0 T e (°C) 12.11 12.11 0 φi (W/m²) 6687.44 6683.2 0.06 φm (W/m²) 5732.09 5731.8 0.01 φe (W/m²) 5422.25 5424.3 0.04 Φ /l (W/m) 12605.52 12610.4 0.04 Comments :


no. 103

THERMAL EVALUATION FORM Software: SolidWorks Simulation Version: 2010 SP0 Computer configuration used: Dell Precision T5500, Windows Vista x64 SP2, Intel Xeon quad core, 16Gb RAM, graphics card NVIDIA Quadro FX 1800. Test name: TWO-MATERIAL PIPE : CONVECTION, THERMAL CONTACT RESISTANCE Codification: TPLA 09-89

Test performed by : Julien BOISSAT Date: 04/11/2009 Model used Finite elements  Boundary elements  Other  Element type : TETRA 10 Number of degrees of freedom or mesh density : Nb of nodes = 12225 Nb of elements = 7767 Nb of DOF = 12225 Results : Physical Deviation Reference value Calculated value (%) quantity T i (°C) 25.11 25.11 0 1 T m (°C) 17.33 17.33 0 2 T m (°C) 5.91 5.91 0 T e (°C) 0.3 0.3 0 φi (W/m²) 6732.90 6732.7 0 φm (W/m²) 5771.06 5770.9 0 φe (W/m²) 5459.11 5459 0 Φ /l (W/m) 12691.23 12690.72 0 Comments :


no. 104

THERMAL EVALUATION FORM Software: SolidWorks Simulation Version: 2010 SP0 Computer configuration used: Dell Precision T5500, Windows Vista x64 SP2, Intel Xeon quad core, 16Gb RAM, graphics card NVIDIA Quadro FX 1800. Test name: SIMPLE WALL : PRESCRIBED TEMPERATURES Codification: TPLL 01-89

Test performed by : Julien BOISSAT Date: 04/11/2009 Model used Finite elements  Boundary elements  Other  Element type : SHELL Number of degrees of freedom or mesh density : Nb of nodes = 5151 Nb of elements = 2500 Nb of DOF = 4949 Results : Location x (m) 0.00 0.01 0.02 0.03 0.04 0.05

Temperature T (°C)

Calculated value

100.0 84.0 68.0 52.0 36.0 20.0

100.0 84.0 68.0 52.0 36.0 20.0

Deviation (%) 0 0 0 0 0 0

Reference value of heat flux from face A to face B φ = 1200 W/m² Calculated value φ = 1200 W/m² Deviation (%) = 0 Comments :


no. 105

THERMAL EVALUATION FORM Software: SolidWorks Simulation Version: 2010 SP0 Computer configuration used: Dell Precision T5500, Windows Vista x64 SP2, Intel Xeon quad core, 16Gb RAM, graphics card NVIDIA Quadro FX 1800. Test name: SIMPLE WALL : PRESCRIBED TEMPERATURES, CONVECTION Codification: TPLL 02-89

Test performed by : Julien BOISSAT Date: 04/11/2009 Model used Finite elements  Boundary elements  Other  Element type : SHELL Number of degrees of freedom or mesh density : Nb of nodes = 5151 Nb of elements = 2500 Nb of DOF = 5050 Results : Location Temperature T (°C) Calculated value x (m) 0.00 73.33 73.33 0.01 62.67 62.67 0.02 52. 52. 0.03 41.33 41.33 0.04 30.67 30.67 0.05 20 20 Reference value of heat flux from face A to face B φ = 800 W/m² Calculated value φ = 800 W/m² Deviation (%) = 0

Deviation (%)

0 0 0 0 0 0

Comments :


no. 106

THERMAL EVALUATION FORM Software: SolidWorks Simulation Version: 2010 SP0 Computer configuration used: Dell Precision T5500, Windows Vista x64 SP2, Intel Xeon quad core, 16Gb RAM, graphics card NVIDIA Quadro FX 1800. Test name: SIMPLE WALL : CONVECTION Codification: TPLL 03-89

A

B

Test performed by : Julien BOISSAT Date: 04/11/2009 Model used Finite elements  Boundary elements  Other  Element type : SHELL Number of degrees of freedom or mesh density : Nb of nodes = 4515 Nb of elements = 2168 Nb of DOF = 4515 Results : Location

Reference value

T A (°C) T B (°C) φ (W/m²)

21.71 416.58 834.2

Calculated value

21.71 416.57 834.27

Deviation(%)

0 0 0

Comments :


no. 107

THERMAL EVALUATION FORM Software: SolidWorks Simulation Version: 2010 SP0 Computer configuration used: Dell Precision T5500, Windows Vista x64 SP2, Intel Xeon quad core, 16Gb RAM, graphics card NVIDIA Quadro FX 1800. Test name: POWER OUTPUT IN A BAR Codification: TPLL 04-89

Test performed by : Julien BOISSAT Date: 04/11/2009 Model used Finite elements  Boundary elements  Other  Element type : SHELL Number of degrees of freedom or mesh density : Nb of nodes = 4221 Nb of elements = 2000 Nb of DOF = 4179 Results : Location x (m) 0.0 0.2 0.5 0.0 0.2 0.5

Reference value

T (°C)

φ (W/m²)

20.0 28.0 32.5 -50.0 -30.0 0.0

Calculated value 20.0 28.0 32.5 -50.0 -30.0 0.0

Deviation (%)

0 0 0 0 0 0

Comments :


no. 108

THERMAL EVALUATION FORM Software: SolidWorks Simulation Version: 2010 SP0 Computer configuration used: Dell Precision T5500, Windows Vista x64 SP2, Intel Xeon quad core, 16Gb RAM, graphics card NVIDIA Quadro FX 1800. Test name: TWO-MATERIAL WALL : CONVECTION Codification: TPLL 05-89

B

C

A


Reference value

T A (°C) T B (°C) T C (°C) φ (W/m²)

25 85 103 -900

Calculated value

25 85 103 -900

Deviation(%)

0 0 0 0

Comments :


no. 109

THERMAL EVALUATION FORM Software: SolidWorks Simulation Version: 2010 SP0 Computer configuration used: Dell Precision T5500, Windows Vista x64 SP2, Intel Xeon quad core, 16Gb RAM, graphics card NVIDIA Quadro FX 1800. Test name: TWO-MATERIAL WALL : CONVECTION, THERMAL CONTACT RESISTANCE Codification: TPLL 06-89 C B2 B1

A Test performed by : Julien BOISSAT Date: 04/11/2009 Model used Finite elements  Boundary elements  Other  Element type : TETRA10 Number of degrees of freedom or mesh density : Nb of nodes = 11542 Nb of elements = 6902 Nb of DOF = 11542 Results : Location

Reference value

T A (°C) T B1 (°C) T B2 (°C) T C (°C) φ (W/m²)

25 85 118.75 136.75 -900

Calculated value

25 85 118.75 136.75 -900

Deviation (%)

0 0 0 0 0

Comments :


no. 110

THERMAL EVALUATION FORM Software: SolidWorks Simulation Version: 2010 SP0 Computer configuration used: Dell Precision T5500, Windows Vista x64 SP2, Intel Xeon quad core, 16Gb RAM, graphics card NVIDIA Quadro FX 1800. Test name: L SHAPED PLATE WITH GEOMETRIC SINGULARITY Codification: TPLP 01-89

Test performed by : Julien BOISSAT Date: 04/11/2009 Model used Finite elements  Boundary elements  Other  Element type : SHELL 6 Number of degrees of freedom or mesh density : Nb of nodes = 3201 Nb of elements = 1536 Nb of DOF = 3103 Results : Reference value T (°C)


Deviation (%)

10 10 10 10 10 7.869 8.018 8.514 9.001 9.316 5.495 5.680 6.667 8.640 9.009 2.816 2.881 2.972 0 0 0

10 10 10 10 10 7.874 8.018 8.516 9.099 9.306 5.496 5.671 6.667 8.658 9.007 2.819 2.882 2.968 0 0 0

0 0 0 0 0 -0.06 0 -0.02 -1.09 0.11 -0.02 0.16 0 -0.21 0.02 -0.11 -0.03 0.13 0 0 0


no. 111

THERMAL

Comments :


no. 112

THERMAL EVALUATION FORM Software: SolidWorks Simulation Version: 2010 SP0 Computer configuration used: Dell Precision T5500, Windows Vista x64 SP2, Intel Xeon quad core, 16Gb RAM, graphics card NVIDIA Quadro FX 1800. Test name: ORTHOTROPIC SQUARE Codification: TPLP 02-89 F

C

B

G

O E

D

H A



no. 113

THERMAL

Point

Reference value T (°C)


Deviation (%)

O A B C D E F G H

22.5 35.0 26.0 10.0 19.0 30.5 18.0 14.5 27.0

22.5 35.0 26.0 9.98 19.0 30.5 18.0 14.5 27.0

0 0 0 0.2 0 0 0 0 0

φ x (W/m²) φ y (W/m²)

45.0 60.0

45.0 60.0

0 0

Comments : In order to apply the convection boundary condition, the edges in short were split in many shorter edged. The convection boundary condition was then applied separately to each one.


no. 114

THERMAL EVALUATION FORM Software: SolidWorks Simulation Version: 2010 SP0 Computer configuration used: Dell Precision T5500, Windows Vista x64 SP2, Intel Xeon quad core, 16Gb RAM, graphics card NVIDIA Quadro FX 1800. Test name: HOLLOW SPHERE: PRESCRIBED TEMPERATURES Codification: TPLV 01-89

Test performed by : Julien BOISSAT Date: 05/11/2009 Model used Finite elements  Boundary elements  Other  Element type : TETRA 10 Number of degrees of freedom or mesh density : Nb of nodes = 7472 Nb of elements = 4441 Nb of DOF = 6229 Results : Reference value Calculated value Deviation (%) r (m) T (°C) φ (W/m²) T (°C) φ (W/m²) 0.3 100.00 1866.67 100.00 1866.80 0 0 0.31 81.94 1748.18 81.94 1748.00 0 0 0.32 65.00 1640.63 65.00 1640.64 0 0 0.33 49.09 1542.70 49.09 1542.66 0 0 0.34 34.12 1453.29 34.12 1453.24 0 0 0.35 20.00 1371.43 20.00 1371.22 0 0 Comments :


no. 115

THERMAL EVALUATION FORM Software: SolidWorks Simulation Version: 2010 SP0 Computer configuration used: Dell Precision T5500, Windows Vista x64 SP2, Intel Xeon quad core, 16Gb RAM, graphics card NVIDIA Quadro FX 1800. Test name: HOLLOW SPHERE: PRESCRIBED TEMPERATURES, CONVECTION Codification: TPLV 02-89

Test performed by : Julien BOISSAT Date: 05/11/2009 Model used Finite elements  Boundary elements  Other  Element type : TETRA 10 Number of degrees of freedom or mesh density : Nb of nodes = 7472 Nb of elements = 4441 Nb of DOF = 6765 Results : Reference value Calculated value Deviation (%) r (m) T (°C) φ (W/m²) T (°C) φ (W/m²) 0.3 65.00 1050 65.00 1050.08 0 0.01 0.31 54.84 983.35 54.84 983.26 0 0.01 0.32 45.31 922.85 45.31 922.86 0 0 0.33 36.36 867.77 36.36 867.75 0 0 0.34 27.94 817.47 27.94 817.45 0 0 0.35 20.00 771.43 20.00 771.31 0 0.02 Comments :


no. 116

THERMAL EVALUATION FORM Software: SolidWorks Simulation Version: 2010 SP0 Computer configuration used: Dell Precision T5500, Windows Vista x64 SP2, Intel Xeon quad core, 16Gb RAM, graphics card NVIDIA Quadro FX 1800. Test name: HOLLOW SPHERE: CONVECTION Codification: TPLV 03-89

Test performed by : Julien BOISSAT Date: 05/11/2009 Model used Finite elements  Boundary elements  Other  Element type : TETRA 10 Number of degrees of freedom or mesh density : Nb of nodes = 11426 Nb of elements = 7294 Nb of DOF = 11426 Results : Physical Calculated Deviation(%) Reference value quantity value T i (°C) 250.28 250.28 0 T e (°C) 184.34 184.34 0 φi (W/m²) 37458.77 37419.4 0.11 φe (W/m²) 21939.36 21924.1 0.07 Φ (W) 42364.87 42304 0.14 Comments :


no. 117

THERMAL EVALUATION FORM Software: SolidWorks Simulation Version: 2010 SP0 Computer configuration used: Dell Precision T5500, Windows Vista x64 SP2, Intel Xeon quad core, 16Gb RAM, graphics card NVIDIA Quadro FX 1800. Test name: TWO-MATERIAL HOLLOW SPHERE : CONVECTION Codification: TPLV 04-89

Test performed by : Julien BOISSAT Date: 05/11/2009 Model used Finite elements  Boundary elements  Other  Element type : TETRA 10 Number of degrees of freedom or mesh density : Nb of nodes = 8936 Nb of elements = 5507 Nb of DOF = 8936 Results : Physical Calculated Deviation (%) Reference value quantity value T i (°C) 25.06 25.06 0 T m (°C) 17.84 17.84 0 T e (°C) 13.16 13.16 0 φi (W/m²) 6740.53 6729.3 0.17 φm (W/m²) 4952.23 4948.2 0.08 φe (W/m²) 4431.32 4439.6 0.19 Φ (W) 7623.36 7610.3 0.14 Comments :


no. 118

THERMAL EVALUATION FORM Software: SolidWorks Simulation Version: 2010 SP0 Computer configuration used: Dell Precision T5500, Windows Vista x64 SP2, Intel Xeon quad core, 16Gb RAM, graphics card NVIDIA Quadro FX 1800. Test name: TWO-MATERIAL HOLLOW SPHERE: CONVECTION, THERMAL CONTACT RESISTANCE Codification: TPLV 05-89

Test performed by : Julien BOISSAT Date: 05/11/2009 Model used Finite elements  Boundary elements  Other  Element type : TETRA 4 Number of degrees of freedom or mesh density : Nb of nodes = 11031 Nb of elements = 7008 Nb of DOF = 11031 Results : Physical Calculated Deviation (%) Reference value quantity value T i (°C) 25.02 25.02 0 1 T m (°C) 17.79 17.79 0 2 T m (°C) 7.87 7.87 0 T e (°C) 3.18 3.18 0 φi (W/m²) 6747.33 6746.84 0.01 φm (W/m²) 4957.22 4957.04 0 φe (W/m²) 4435.79 4435.46 0.01 Φ (W) 7631.04 7630.6 0.01 Comments :


no. 119

THERMAL EVALUATION FORM Software: SolidWorks Simulation Version: 2010 SP0 Computer configuration used: Dell Precision T5500, Windows Vista x64 SP2, Intel Xeon quad core, 16Gb RAM, graphics card NVIDIA Quadro FX 1800. Test name: POWER OUTPUT IN A HOLLOW SPHERE Codification: TPLV 06-89

Test performed by : Julien BOISSAT Date: 05/11/2009 Model used Finite elements  Boundary elements  Other  Element type : TETRA 10 Number of degrees of freedom or mesh density : Nb of nodes = 11309 Nb of elements = 7491 Nb of DOF = 9895 Results : Reference value Calculated value Deviation (%) r (m) T (°C) Φ (W) T (°C) Φ (W) 1.0 20.00 -837.8 20.00 -833.12 0 0.56 1.2 29.33 -532.8 29.33 -527.8 0 0.94 1.5 32.50 157.1 32.50 159.07 0 1.25 Comments :


no. 120

THERMAL EVALUATION FORM Software: SolidWorks Simulation Version: 2010 SP0 Computer configuration used: Dell Precision T5500, Windows Vista x64 SP2, Intel Xeon quad core, 16Gb RAM, graphics card NVIDIA Quadro FX 1800. Test name: ORTHOTROPIC CUBE Codification: TPLV 07-89

Test performed by : Julien BOISSAT Date: 05/11/2009 Model used Finite elements  Boundary elements  Other  Element type : TETRA 10 Number of degrees of freedom or mesh density : Nb of nodes = 67128 Nb of elements = 46779 Nb of DOF = 67128


no. 121

THERMAL Results : Point

O A B C D E F G H I J K L M N P Q R S φ x (W/m²) φ y (W/m²) φ z (W/m²)

Reference value T (°C) 22.5 35.0 26.0 10.0 19.0 30.5 18.0 14.5 27.0 29.0 20.0 4.0 13.0 16.5 41.0 32.0 16.0 25.0 28.5 45.0 = Cte 60.0 = Cte 30.0 = Cte

Calculated value T (°C) 22.5 35.0 26.0 10.0 19.0 30.5 18.0 14.5 27.0 29.0 20.0 4.0 13.0 16.5 41.0 32.0 16.0 25.0 28.5 45.0 60.0 30.0

Deviation (%)

0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0

Comments : In order to satisfy the boundary conditions, we had to split the faces and apply the convection separately to each small face because the software does not allow ambient temperature variation for convection as a boundary condition.


no. 122

THERMAL

2. Non linear steady state thermal

EVALUATION FORM Software: SolidWorks Simulation Version: 2010 SP0 Computer configuration used: Dell Precision T5500, Windows Vista x64 SP2, Intel Xeon quad core, 16Gb RAM, graphics card NVIDIA Quadro FX 1800. Test name: PIPE : CONVECTION, RADIATION Codification: TPNA 01-89

Test performed by : Julien BOISSAT Date: 05/11/2009 Model used Finite elements  Boundary elements  Other  Element type : TETRA 10 Number of degrees of freedom or mesh density : Nb of nodes = 8340 Nb of elements = 5113 Nb of DOF = 8340 Results : Physical Reference value Calculated value Deviation (%) quantity T i (°C) 105.55 104.7 0.81 T e (°C) 82.56 81.93 0.77 φi (W/m²) -11577.49 -11455 1.05 φe (W/m²) -8822.98 -8790.3 0.37 Φ (W) 21807.15 21586 1.01 Comments :


no. 123

THERMAL EVALUATION FORM Software: SolidWorks Simulation Version: 2010 SP0 Computer configuration used: Dell Precision T5500, Windows Vista x64 SP2, Intel Xeon quad core, 16Gb RAM, graphics card NVIDIA Quadro FX 1800. Test name: SIMPLE WALL : CONVECTION, RADIATION Codification: TPNL 01-89

B

A Test performed by : Julien BOISSAT Date: 05/11/2009 Model used Finite elements  Boundary elements  Other  Element type : SHELL Number of degrees of freedom or mesh density : Nb of nodes = 4515 Nb of elements = 2168 Nb of DOF = 4515

Results :

Location

Reference value

T A (°C) T B (°C) φ (W/m²)

28.56 488.27 971.20

Calculated value

28.55 488.15 971.05

Deviation (%)

0.04 0.02 0.02

Comments :


no. 124

THERMAL EVALUATION FORM Software: SolidWorks Simulation Version: 2010 SP0 Computer configuration used: Dell Precision T5500, Windows Vista x64 SP2, Intel Xeon quad core, 16Gb RAM, graphics card NVIDIA Quadro FX 1800. Test name: RADIATION IN A SQUARE CAVITY Codification: TPNP 01-89

3

3


Reference value T (K)

Calculated value

Deviation (%)

Lateral face (3)

1192

1208.5

1.38

Comments :


no. 125

THERMAL EVALUATION FORM Software: SolidWorks Simulation Version: 2010 SP0 Computer configuration used: Dell Precision T5500, Windows Vista x64 SP2, Intel Xeon quad core, 16Gb RAM, graphics card NVIDIA Quadro FX 1800. Test name: HOLLOW SPHERE: CONVECTION, RADIATION Codification: TPNV 01-89

Test performed by : Julien BOISSAT Date: 05/11/2009 Model used Finite elements  Boundary elements  Other  Element type : TETRA10 Number of degrees of freedom or mesh density : Nb of nodes = 11367 Nb of elements = 7262 Nb of DOF = 11367 Results : Physical Calculated Deviation (%) Reference value quantity value T i (°C) 91.74 91.04 0.77 T e (°C) 71.13 70.70 0.61 φi (W/m²) 11666.60 11545 1.05 (1) φe (W/m²) 6825.85 6763.6 0.92 Φ (W) 13194.61 13050.4 1.08 Comments : (1) Typo in the validation guide. Reference value φe was checked with the formula φe = he (T e – T ee )


no. 126

THERMAL EVALUATION FORM Software: SolidWorks Simulation Version: 2010 SP0 Computer configuration used: Dell Precision T5500, Windows Vista x64 SP2, Intel Xeon quad core, 16Gb RAM, graphics card NVIDIA Quadro FX 1800. Test name: RADIATION IN A CUBIC CAVITY Codification: TPNV 02-89


Location

Reference value T (K)

Calculated value T (K)

Deviation (%)

Face (3) lateral

1214

1218

0.30

Comments :


no. 127

THERMAL

3. Transient linear THERMAL

EVALUATION FORM Software: SolidWorks Simulation Version: 2010 SP0 Computer configuration used: Dell Precision T5500, Windows Vista x64 SP2, Intel Xeon quad core, 16Gb RAM, graphics card NVIDIA Quadro FX 1800. Test name: CYLINDER : HEAT TRANSFER BY CONVECTION Codification: TTLA 01-89

Test performed by : Julien BOISSAT Date: 05/11/2009 Model used Finite elements  Boundary elements  Other  Element type : SHELL Number of degrees of freedom or mesh density : Nb of nodes = 1325 Nb of elements = 630 Nb of DOF = 1325 Results : Reference values Calculated value T (°C) T (°C) Time (s) On surface At center On surface At center 600 461 314 459 326 800 550 412 539 424 1000 637 510 607 508 1200 686 588 665 580 1400 735 657 714 642 1600 774 706 756 694 1800 813 755 792 739 2200 873 828 848 810 2600 910 880 889 862 3000 936 917 920 899 3400 951 941 941 927 3800 970 959 957 947

Deviation (%)

0.35 1.97 4.73 3.13 2.89 2.36 2.64 2.84 2.25 1.76 1.01 1.30

3.96 2.91 0.36 1.32 2.32 1.66 2.10 2.17 2.08 1.93 1.52 1.29

Comments :


no. 128

THERMAL EVALUATION FORM Software: SolidWorks Simulation Version: 2010 SP0 Computer configuration used: Dell Precision T5500, Windows Vista x64 SP2, Intel Xeon quad core, 16Gb RAM, graphics card NVIDIA Quadro FX 1800. Test name: WALL UNDER THERMAL SHOCK Codification: TTLL 01-89

Test performed by : Julien BOISSAT Date: 05/11/2009 Model used Finite elements  Boundary elements  Other  Element type : SHELL Number of degrees of freedom or mesh density : Nb of nodes = 1111 Nb of elements = 500 Nb of DOF = 1100 Results : T ( x,t ) n=45 t (s)

Reference values x (m) 0.2 0.4 0.6

Calculated values x (m) 0.2 0.4 0.6

Deviation (%) x (m) 0.2 0.4 0.6

0.1

65.48

37.14

18.15

53.37

28.81

16.16

4.56

7.74

4.88

0.2

75.58

53.84

36.96

70.80

48.07

32.91

1.29

2.57

3.09

0.3

81.19

64.25

50.85

78.59

60.18

46.52

0.67

1.47

2.24

0.4

85.33

72.10

61.61

83.39

68.65

57.25

0.54

1.19

1.87

0.5

88.54

78.21

70.00

86.84

75.04

65.77

0.48

1.05

1.59

0.6

91.05

82.97

76.56

89.49

80.04

72.56

0.44

0.92

1.37

0.7

93.01

86.69

81.69

91.59

84.00

78.00

0.40

0.80

1.18

0.8

94.53

89.60

85.69

93.26

87.18

82.35

0.34

0.69

1.00

0.9

95.73

91.88

88.82

94.59

89.72

85.85

0.30

0.60

0.86

1

96.66

93.65

91.26

95.66

91.75

88.65

0.26

0.51

0.72

1.2

97.96

96.13

94.67

97.21

94.69

92.70

0.19

0.37

0.52


no. 129

THERMAL 1.4

98.76

97.63

96.74

98.21

96.59

95.30

0.14

0.26

0.36

1.6

99.24

98.56

98.01

98.85

97.80

96.98

0.09

0.19

0.25

1.8

99.54

99.12

98.79

99.26

98.59

98.06

0.07

0.13

0.18

2

99.72

99.46

99.26

99.52

99.09

98.75

0.05

0.08

0.12

T ( x,t ) n=45 t (s)

0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1 1.2 1.4 1.6 1.8 2

Reference values x (m)

0.8 8.09 26.37 42.27 54.87 64.74 72.45 78.47 83.18 86.86 89.73 93.73 96.17 97.66 98.57 99.13

1 5.07 22.77 39.32 52.55 62.92 71.03 77.36 82.31 86.18 89.20 93.41 95.98 97.54 98.50 99.08

Calculated values x (m)

0.8 10.20 24.46 38.26 50.11 59.87 67.78 74.14 79.26 83.36 86.65 91.41 94.48 96.45 97.71 98.53

1 8.45 21.77 35.51 47.69 57.85 66.13 72.82 78.19 82.51 85.97 90.97 94.19 96.26 97.60 98.45

Deviation (%) x (m)

0.8 10.30 2.49 2.81 2.41 2.03 1.71 1.44 1.22 1.03 0.87 0.61 0.43 0.29 0.20 0.14

1 28.06 1.84 3.03 2.62 2.18 1.83 1.53 1.29 1.09 0.92 0.65 0.46 0.31 0.21 0.14

t=2s Comments :


no. 130

THERMAL EVALUATION FORM Software: SolidWorks Simulation Version: 2010 SP0 Computer configuration used: Dell Precision T5500, Windows Vista x64 SP2, Intel Xeon quad core, 16Gb RAM, graphics card NVIDIA Quadro FX 1800. Test name: PLATE : HEAT TRANSFER BY CONVECTION Codification: TTLL 02-89

Test performed by : Julien BOISSAT Date: 05/11/2009 Model used Finite elements  Boundary elements  Other  Element type : SHELL Number of degrees of freedom or mesh density : Nb of nodes = 10251 Nb of elements = 5000 Nb of DOF = 10251 Results : Time (s)

800 1000 1500 2000 2500 3000 3500 4000 5000 6000 7000 8000

Reference temperatures(°C) On surface At center 412 264 461 314 559 451 647 550 711 637 764 710 814 765 848 813 902 877 936 920 958 948 972 966

Calculated temperatures(°C) On surface At center 394 245 441 303 544 432 628 536 696 621 752 691 798 748 835 794 890 863 927 909 951 939 968 960

Deviations (%)

4.45 4.30 2.68 2.95 2.06 1.54 1.99 1.53 1.32 0.98 0.70 0.46

7.33 3.34 4.31 2.52 2.44 2.66 2.23 2.30 1.59 1.22 0.92 0.67

Comments


no. 131

THERMAL EVALUATION FORM Software: SolidWorks Simulation Version: 2010 SP0 Computer configuration used: Dell Precision T5500, Windows Vista x64 SP2, Intel Xeon quad core, 16Gb RAM, graphics card NVIDIA Quadro FX 1800. Test name: SPHERE : HEAT TRANSFER BY CONVECTION Codification: TTLV 01-89

Test performed by : Julien BOISSAT Date: 05/11/2009 Model used Finite elements  Boundary elements  Other  Element type : TETRA 10 Number of degrees of freedom or mesh density : Nb of nodes = 23397 Nb of elements = 15885 Nb of DOF = 23397 Results : Reference temperature Calculated value T (°C) T (°C) Time (s) On surface At center On surface At center 400 461 334 458 323 600 608 500 577 470 800 696 618 670 586 1000 774 706 742 677 1200 828 774 799 748 1400 868 828 843 803 1600 902 872 877 846 1800 923 902 904 880 2000 942 923 925 906 2200 956 942 942 927 2400 962 956 954 943

Deviations (%)

0.65 5.07 3.74 4.09 3.52 2.88 2.73 2.02 1.77 1.50 0.78

3.41 6.05 5.19 4.15 3.41 3.02 2.96 2.45 1.81 1.61 1.37

Comments :


no. 132

III.

THERMOMECHANICS


no. 133

THERMOMECANICS

1. Linear static EVALUATION FORM Software: SolidWorks Simulation Version: 2010 SP0 Computer configuration used: Dell Precision T5500, Windows Vista x64 SP2, Intel Xeon quad core, 16Gb RAM, graphics card NVIDIA Quadro FX 1800. Test name: THICK PIPE SUBMITTED TO A THERMAL GRADIENT Codification: HSLA 03-89

Test performed by : Julien BOISSAT Date: 05/11/2009 Model used Finite elements  Boundary elements  Other  Element type : TETRA 10 Number of degrees of freedom or mesh density : Nb of nodes = 11361 Nb of elements = 7238 Nb of DOF = 34083 Results : Physical quantity and Location Calculated value reference unit σ θ (Pa) -100.86 × 10 6 -100.80 × 10 6 σ z (Pa) -130.26 × 10 6 -130.28 × 10 6 r = Ri ur (m) 7.644 × 10 -6 7.644 × 10 -6 σ θ (Pa) 42.00 × 10 6 42.00 × 10 6 σ z (Pa) 12.6 × 10 6 12.60 × 10 6 r = Re ur (m) 30.6 × 10 -6 30.577 × 10 -6

Deviation (%)

0.06 0.02 0.00 0.00 0.00 0.08

Comments :


no. 134

IV.

BIBLIOGRAPHY


no. 135

BIBLIOGRAPHY

Title : Guide de validation des progiciels de calcul de

structures Author : Société Française des Mécaniciens Editor : Association Française de Normalisation (AFNOR)

Roark and Thimoshenko books are classic references used by many engineers.

Language : French ISSN: 0297-4827 ISBN-10: 2124866117 ISBN-13: 978-2124866113

Title : ROARK’s Formulas for Stress & Strain 6 th edition Author : Warren C. Young Editor : McGRAW-HILL INTERNATIONAL EDITIONS Language : English ISBN-10: 0071003738

Title : Théorie des plaques et coques (Theory of plates and

shells) Author : S. Timoshenko, S. Woinowsky-Krieger Editor : DUNOD Language : French Library polytechnique Ch. Beranger N° 5768 – 2nd trimestre

1968


no. 136

SolidWorks Simulation 2010 Validation

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