Cessna 172 Design

Cessn essna Skyh Skyhaw awk I I / 100 Perf er f orm or mance Assess essment

Pr epar epar ed by by

J ohn McI ver B. Eng. ( Aer o) Tempor al I mages

23r d J anuar y 2003

ht t p: / / www. t empor al . com. au

Cess Cessna na Skyhaw Skyhawk I I / 100 100 ( 172) 172) Per Per f orm or mance Assess ss essm ment ent

1. I nt rodu roducti on Thi s document out l i nes t he i nf or mat i on and pr ocedur es used t o det er mi ne t he appr oxi mat e per f or mance of t he Cess na 172 ai r craf t . As much aer aer odyn odynam ami c and and di di mensi ensi onal onal i nfor mati on as possi possi bl e was f i r st obt obt ai ned ned fr om several several sour sour ces and and t hat hat dat dat a i s presen presentt ed i n the f ol l owi ng secti secti on. on. Whi l e the Cessna Cessna 172 172 model odel was t he t arget ai r cr af t , i t was necessar necessar y to obtai n som some data data f r om other r el ated model odel s whe wherr e dat dat a speci speci f i cal l y f or a model odel 172 was not not avai avai l abl abl e. Addi ddi t i onal onal l y there ar ar e seve severr al subsub- model odel s of t he 172 172, so wher her e possi possi bl e data data was obtai obtai ned ned f or a Cessna Cessna Skyha Skyhaw wk I I / 100, 100, t hi s bei bei ng a l at er vers i on of t he gene generr i c model odel 172. 172. Tai l dat a was obt ai ned f or a model 177, 177, as 172 dat a was not avai l abl e. I n t hi s cas e t he 177 has a sl i ght l y s mal l er t ai l , but t he gene generr al desi desi gn f eat eat ures shoul shoul d be be equi equi val val ent ent t o t he 172. 72. A comput put er pr ogr ogr am was t hen hen used used t o obtai obtai n a r ange ange of per per f ormance ance dat dat a based based on speci f i c i nput nput data der der i ved f r om t he vari ous ous r efer ence ence sour sour ces. The The com comput put er pr ogr ogr am coul coul d outpu outputt per per f ormance ance ove overr a range range of speed speeds s and al t i t udes, udes, al l owi ng i t erat i on of t he i nput nput data, so i t was possi possi bl e to obt obt ai n a dat dat a set set whi ch woul oul d cl osel osel y equ equate ate t o the defi defi ned ned ai ai r craf t per per f ormance. ance. A copy copy of t he fi nal pr ogram ogram out out put i s i ncl uded ded here.

2. Ref erence erence Data Data As much data as possi bl e was obtai ned by ref er ence t o a num number of t ext books. The key ref er ence was t aken t o be J be J ane' ane' s Al l t he W orl d' s Ai Ai rcr aft , wi t h more det det ai l ed dat dat a sour sour ced f r om other books. books. The The com compl et e set set of dat dat a whi ch was obt obt ai ned ned i s presented here.

2. 1. J ane' s Al Al l t he Worl d' s Ai Ai rcr af t 1977- 78 For t he Cessna Cessna Skyh Skyhaw awk I I / 100 100 the f ol l owi ng dat dat a was presented; NACA 2412 wi ng se sec t i on

www t empor al com au

1 degr e e 44 44 mi nut e s di di hedr a l 1 degree degree 30 mi nut nut es i nci dence dence at wi wi ng r oot - 1 deg degrr ee 30 mi nut nut es i nci nci dence dence at t i p Modi f i e d F r i s e ai ai l er o ns ns Si ngl e s l ot t ed f l aps Page 1

Ver t i ca cal Ta T ai l :

35 degr ee ees quar t er er ch chor d s weep

Engi ne ne: Pr opel l or or : F uel Ca Capac i t y: y: Baggage Capac i t y: y:

160 hp L yc omi ng n g O- 32 320- H ( max power at 27 2700 r pm pm) Two bl ad aded f i x ed pi t c h met al pr pr opel l or or 43 US gal l ons ( 38 38 US gal l ons us abl e) e) 120 pounds

Pri nci nci pl e Di mensi ensi ons ons Wi ng Wi ng ng Wi ng ng Wi ng ng

s pan: r oot c hor d: t i p c hor d: as pec t r at i o: o:

L engt h over al l : Hei gh ght over al l : Tai l pl ane span: Pr op opel l or di di am a met er er : Wi ng ar ea: Ai l er on Ar ea: F l ap Ar ea: Ver t i c al Ta T ai l Ar ea ea: Rudder Ar ea: Hor i z on ont al al Tai l Ar ea ea: El ev evat or Ar ea:

35 f eet 10 i nc hes 5 f ee eet 4 i nc nc hes 3 f eet 8. 5 i nc nc hes 7. 52 26 f eet 11 i nc nc hes 8 f eet 9. 5 i nc nc hes 11 f eet 4 i nches 6 f ee eet 3 i nc n c hes 174 s quar e f eet ( gr os s ) 18. 3 s quar e f eet 21. 2 s quar e f eet 11. 24 24 s quar e f ee eet 7. 43 s quar e f eet 21. 56 5 6 s qu quar e f ee e et 14. 53 53 s quar e f eet

Wei ght Dat a Wei ght - Empt y Eq Equi pped pped:: Max Tak eof f Wei gh g ht : Max Wi ng L oadi ng: Max Power Lo Loadi ng:

1403 2300 13. 2 14. 4

poun ounds pounds pounds per sq s quar e f ee e et pounds per ho hor s ep epower

Per f or mance Dat a Never Ex Exc eed Speed: Max L evel Sp Speed: Max Cr ui u i s i ng Speed: St al al l i ng n g Speed: St al al l i ng Speed: www t empor al com au

174 mph 144 mph ( at at SL SL ) 140 mph ( 75 75% power at at 80 8000 f e et et ) 57 mph CAS ( f l ap a ps up) 51 mph CAS ( f l ap a ps down) Page 2

Max Rat e of Cl Cl i mb: Ser vi ce ce Cei l i ng ng:

770 f ee e et pe per mi nut e ( at at SL SL ) 14, 20 200 f eet

Range Per f or mance 558 mi l es r ange ange at 8, 000 f eet eet crui se 662 662 mi l es range at 10, 000 000 f eet eet cr ui es ( usi ng st anda andarr d f uel uel , wi t h al l owance ance f or engi engi ne st art , t axi axi , t akeoff akeoff , cl i mb, and 45 mi nut nut es reserve at 45% 45% pow power)

2. 2. Fl ui d Dynam ynami c Dr ag by by Hoerner Thi s book i ncl udes a ver y basi c dr ag anal ys i s of a Cessna 172, 172, based on t he f ol l owi ng i nf or mat i on. Span: Wi ng Ar ea e a: Wei gh g ht : Power :

36 f eet 175 s qu quar e f ee e et 2200 pounds 140 hor se sepower

At a vel vel oci oci t y of of 122 kno knott s and and sea sea l evel evel t he ai ai rcr aft was cal cal cul cul ated t o hav have e a t otal drag coeff coeff i ci ent ent of 0. 032, a pr pr ofi l e drag drag coef coef f i ci ent ent of 0. 029 and and a dr dr ag coef coef f i ci ent ent based based on wett ed surf ace area of of 0. 009. 09. Thi s i s basi c dat a f or a Cess na 170, whi ch i s not t he ai r cr af t bei ng anal ys ed her e. As i t i s a si mi l ar desi gn, t hi s dat a can be used used t o approxi approxi matel y veri f y any any drag dat dat a we may be be abl abl e t o cal cul ate f or t he Cessna Cessna 172 172..

2. 3. Syn Synt hesi s of Subsoni soni c Ai Ai r pl ane ane Desi gn by Toren Torenb beek eek Thi s book pr ovi des many gener al r ul es f or pr el i mi nar y ai r cr af t desi gn cal cul at i ons. The key per f or mance dat a whi ch i s r el evant her e i s t hat a t y pi pi c al al s mal l , s i ngl e en engi ne ai ai r c r a f t , wi t h a f i x ed ed un under c a r r i age, wi l l hav e a pr pr o f i l e dr dr a g c oe oef f i c i ent somewher her e bet bet ween 0. 025 025 and and 0. 040. 040. The The Osw Oswal al d spanw spanwi se ef f i ci ency ency f actor wi l l l i e bet bet ween 0. 65 and and 0. 0. 75. 75. The book al s o pr ovi des a number of t abl es of r epr ese nt at i ve dat a f or var i ous ai r cr af t , f or wi ng, hor i zont al and ver t i cal par par ameter s, and and al so wei wei ght ght dat dat a.


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t ai l

Wi ng dat dat a f or a Cessna Cessna 172 172 Pr ot ot ot ot yp ype f i r s t f l i ght : As pec t Rat i o: Taper Rat i o: Quar uar t er Cho Chorr d Sweep eep Angl ngl e: Geomet r i c Twi st st : Di hedr al : Sec t i on Pr of of i l e - Ro Root : Sec t i on Pr of of i l e - T i p : Thi cknes s/ Chor Chor d Rat i o:

1956 7. 52 0. 672 0 degrees degrees - 3. 3. 0 degr ees 1 degr ee 44 mi nut es NACA 2412 NACA 2412 t o s ym ymmet r i c 12 per cent

Vmo: Vd:

224 k mh ( EAS) Maxi mum Oper at i ng ng L i mi t 280 k mh ( EAS) Des i gn Di ve

F l ap Type: Cf / C St r ea eamwi s e: e: Bf / B: F l ap a p Angl e - Ta T ak eof f : F l ap Angl e - La L andi ng: Cl max - L andi ng ng:

s i ngl e s l ot t ed 32. 9 per ce cent ( f l ap ap c hor d r at at i o) o) 46. 1 per c ent ( f l ap s pan r at i o) 20 degr ee ees 40 degr ee ees 2. 10 10 ( f r om f l i gh ght t es t )

Wei ght Dat Dat a f or Cess na 172 172B B MTOW:

2200 pounds

Wi ng Gr oup: Tai l Gr oup: F us el ag age Gr oup: L andi ng Gear : Sur f ac ac e Cont r ol s: s: Nac el l e Gr oup: Pr opul si si o on n Gr oup: Engi ne n e I ns n s t al al l at i on o n: F uel Sys t em: Exhaus t : Ot her I t ems : Servi Servi ces/ ces/ Equi pment ent Group: roup: Nav I ns ns t r ument s : Hydr au aul i c / P Pn neumat i c : El ec t r i c al : www t empor al com au

236 pounds 61 pounds 253 pounds 122 pounds 31 pounds 31 pounds 427 pounds 312 pounds 30 pounds 38 pounds 47 pounds 154 pou poun nds 7 pounds 3 pounds 41 pounds Page 4

F ur ni s hi ng: Ai r c ond/ Ant i - i ce ce:

99 pounds 4 pounds

Payl oad Gr oup Pi l o t : Pas s enger : F uel : Ot her :

165 pounds 165 pounds 252 pounds

( 43 US gal l on ons at 5. 85 85 pounds per US gal l on on)

303 pounds ( c ar go, oi l , et c )

Wei ght and CG CG Dat a f or Cess na 172 172 ( nor mal cat egory FAR 23) 23) ( CG posi posi t i ons ons ar e i n per per cent cent of mean ean aer aer odyna odynam mi c chord) F or or wa war d CG CG L i mi t - T ak ak eo eof f / L an andi ng: F or war d CG L i mi t - Fl Fl i gh ght :

15. 6 15. 6

Rear CG CG L i mi t - Tak eof f / L an andi ng: Rear CG L i mi t - F l i ght :

36. 5 36. 5

CG Range - Ta Tak eof f / La Landi ng ng: CG Range - F l i ght :

20. 9 20. 9

Payl oad: Tai l Vol ume: Hor i zo zont al Tai l Type: Cl max:

64. 3 ( per c ent OEW) 0. 59 F i xe xed St abi l i se ser 2. 14 ( f l ap angl e f or l andi ng)

Hori zont zont al Tai Tai l Data f or Cessn Cessna a 17 177 Sh/ S: As pec t Rat i o: Taper Rat i o: Sweep: Ai r f oi l Sec t i on: Aver age T/ C: Tai l Type: Hor i zo zont al Tai l Vol um ume: Hi nge Pos i t i on: Servo Tab Tabs f i t t ed


0. 202 4. 00 1. 0 0. 0 degr ees NACA 0012/ 0009 10. 5 per c ent Al l Fl yi ng 0. 600 25 per c ent El evat or Chor d

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Vert i cal Tai Tai l Data f or Cessn Cessna a 17 177 Max Cr os s wi nd: Sv/ S: As pec t Rat i o: Sweep: Ai r f oi l Sec t i on: Aver age T/ C: Ver t i c al Tai l Vol ume: Sr / Sv: Hi nge Pos i t i on:

20 k not s 0. 107 1. 41 35 degr ees ( quar t er c hor d) NACA 0009/ 0006 7. 5 per c ent 0. 0411 0. 368 60 per c ent Cv ( r oot / t i p)

Note: The The Cessna Cessna 177 177 h has as a sl i ght ght l y smal l er t ai l t han han the Cessna Cessna 172 172 Tai l Ar eas F i n: n: Rudder : Tai l pl ane: El ev e vat or or s: s: Hor i z ont al Tai l :


11. 24 24 s q. f t ( Ces s na 172) 7. 43 43 s q. f t ( Ces s na 172) 21. 56 sq. f t ( Cess na 172) 14. 53 53 s q. f t ( Ce Ces s na 172)

11. 02 02 s q. f t ( Ces s na 177) 6. 41 41 s q. f t ( Ces s na 177)

35. 01 s q. f t ( Ces s na 177)

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3. Comput er Anal ysi s A comput put er pr ogr ogr am was t hen hen used used to i t erat e to a sui t abl abl e set of dat dat a val val ues ues whi whi ch woul oul d b be e representat i ve of of t he Cessna 172. 172. Thi s pr ogr am i s a si mpl e ai r cr af t per f or mance pr ogr am, wr i t t en about 20 year s ago, f or oper at i on on Per sonal Comput er s r unni ng MS DOS. I t s most usef ul f eat eat ure i s t hat hat , based based on ver ver y basi basi c i nput nput dat dat a, i t can produc produce e data data f or any any al al t i t ude, ude, f or a r ange ange of ai r speeds. speeds. Thi s f aci l i t y al l ows f or r api api d checki checki ng of est i mated per per f ormance ance dat dat a agai agai nst publ publ i shed shed val val ues. ues. Fr om t he ref erence dat dat a obt obt ai ned ned the f ol l owi ng val ues ues w were ere used as as i nput nput t o t he com comput put er per per f ormance ance program. St a l l s sp peed wi t ho hout f l ap aps Maxi mum l i f t c oef f i ci c i en ent Maxi mum l i f t c oef f i ci ci e en nt Maxi mum t ak e- of f wei gh ght Empt y wei ght Wi ng s pan Ai r pl an ane ef f i ci ci en enc y f ac t or Engi ne ne br ak e hor s epower Maxi mum l evel s peed Pr opel l or di amet er Pr opel l or s peed

57. 0 mph 1. 60 60 ( no f l aps ) 2. 10 10 ( wi t h f l ap aps ) 2300 l b 1403 l b + pi l ot at 165 l bs 35. 83 f t 0. 77 77 160 hp 144. 0 mph 75. 0 i nc hes 2700 r pm

The engi ne i s not super char ged F i xed- pi t c h pr pr o pe pel l or f i t t ed t o ai ai r c r a f t Number ber of pr pr opel opel l ors: 1 Aver ver age age r ange ange propul propul si ve eff i ci ency ency Av er er a ge ge en endur a nc nc e pr pr o pu pul s i v e e f f i c i enc y Ai r c r af t pr pr opul si s i ve ve ef f i ci c i en enc y

0. 700 700 0. 700 0. 85 850

The above dat a i s t hat used f or t he f i nal comput er anal ys i s. Ear l i er r uns used sl i ght l y di f f er ent dat a, whi ch was sl owl y adj adj ust ed unti l t hi s dat dat aset aset gave ave what were were con consi dered as acce accep pt abl abl e resul resul t s. The The f i nal out out put put f rom t he program program i s i ncl uded her e as Appen Appendi di x A. A.


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4. Dr ag Summar y The t ot al ai r cr af t dr ag coef f i ci ent , based on a gr os s wi ng ar ea of 174 squar e f eet , was 0. 0341, 0341, gi vi ng a dr ag ar ea ( CdS) CdS) of 5. 9334 9334 squar squar e f eet. Thi Thi s val ue of 0. 0341 0341 corr espond esponds s accept accept abl abl y wi t h the val val ue det det ermi ned ned by by Hoer ner ner f or t he Cessna Cessna 170 170 of of 0. 032. 032. Br eaki eaki ng t he drag dow down i nto i t s compone ponent nt part s, f or wi wi ng, ng, t ai l and and fusel age, age, we know know t he t otal ai r cr aft drag val val ue, ue, and and can can al so obtai obtai n esti mates of t he drag coef coef f i ci ent ent f r om NACA graphs graphs for t he par par t i cul cul ar wi ng secti ons ons used used.. Usi ng Theor Theory y of W i ng Sect i ons by Abbot bbot t and Von Doenhof oenhof f t o obtai obtai n the sect sect i on drag dat dat a (assumed t o be be "st anda andarr d roughn roughness" ess" r ather t han han val val ues ues f or l ami nar f l ow) , Wi ng ( NA NACA 2412) Tai l ( NACA ACA 0012) 0012) F i n ( NA NACA 0009) Tot al Ai r cr af t

Cd Cd Cd Cd

= = = =

0. 0100 0. 0098 0098 0. 0092 0. 0341 0341

S S S S

= = = =

174. 0 21. 56 11. 24 174. 0

sq sq sq sq sq

ft ft ft ft

CdS CdS CdS CdS CdS CdS

= = = =

1. 74 0. 21 0. 10 10 5. 93

sq sq sq sq

ft ft ft ft

Subt racti ng the wi ng an and tai l / f i n val val ues f rom t he tot al ai rcr aft gi ves ves us t he drag drag of of t he f usel age age and and any any ot ot her mi scel scel l aneo aneous us i t e ms ( under c a r r i age, s t r ut s , et c ) , whi c h i s , 5. 93 - 0. 10 - 0. 21 - 1. 74 = 3. 88 squa squarr e f eet eet Thi s t hen becomes 3. 88 / 174 = 0. 0223, 0223, bei ng t he dr ag coef f i ci ent f or t he f usel age based on gr os s wi ng ar ea. We can al so est i mat e t he wet t ed surf ace area based on the Hoer ner ner anal anal ysi s, where the areas areas wi wi l l be i n i nverse verse r ati on t o the dr a g c oe oe f f i c i ent s . Us i ng hi hi s d r ag ag co coe f f i c i ent s , Cd = 0. 009 009 based based on wett ed sur sur f ace ar ar ea (t o be found) found) Cd = 0. 032 032 b based ased on wi ng ar ar ea (174. (174. 0) So wett ed sur sur f ace ar ar ea = ( 0. 032 032 / 0. 009 009) x 174 174. 0 = 618. 7 squa squarr e f eet eet approxi approxi matel y.


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5. Program rogram Val i dat i on The out put f r om t he comput er pr ogr am i s onl y appr oxi mat e i n i t s model l i ng of t he Cess na 172 per f or mance, t he publ publ i shed shed perf perf ormance ance data data f or t he ai r cr aft i n most ar eas. eas.

but does agr ee wi t h

At seal seal l evel evel t he predi predi ct ed speed speed r ange ange i s f r om sl i ght ght l y l ess t han han 57 57 mph t o nea nearr l y 1 14 40 mph, ph, compar par ed t o the pub publl i shed shed data data of 57 mph t o 144 mph. The ser vi ce cei l i ng i s def i ned as t he al t i t ude wher e t he r at e of cl i mb of t he ai r cr af t decl i nes t o 100 f eet per mi nut e, and i s quoted quoted for t he Cessna essna as as 14, 14, 200 feet. At 14, 14, 200 feet f r om t he progr progr am out out put put t he i ndi ndi cated maxi axi mum cl i mb rat e i s 111 111 feet per mi nute. The quot ed maxi mum r at e of cl i mb at sea l evel of 770 f eet per mi nut e compar es wi t h a pr ogr am pr edi ct i on of 689 f eet per mi nut e. The quot ed maxi mum cr ui si ng speed of 140 mph, at 75 per cent power at 8, 000 f eet , i s not achi evabl e acc or di ng t o t he pr ogr am, i ndi cat cat i ng t he drag drag esti mate i s possi possi bl y a l i t t l e too hi gh. gh. Al t ernati ernati vel vel y thi s cou coul d i ndi cat cat e that that t he actua actuall eng engi ne pow power decreases decreases wi t h al t i t ude ude at at a sl ower r ate than t hat hat pr edi edi ct ed by t he progr progr am. I n practi ce t hi s di di scr epan epancy cy i s pr pr obab obabll y part part l y due due t o bot bot h causes. causes. Al t houg hough h the range range cal cul ati ons ons of t he progr progr am are onl onl y ver ver y app apprr oxi oxi mate, at 8, 000 f eet eet i t predi predi ct s a range range of of 584 mi l es compar par ed t o the pub publl i shed shed f i gur gur e of of 558 mi l es, whi l e at at 10, 000 feet i t predi predi ct s a f i gur gur e of of 539 mi l es, compar par ed t o 66 662 mi l es f or t he publ publ i shed shed data. data. Thi Thi s anal anal ysi s i s necessa necessarr i l y onl onl y app apprr oxi oxi mate as no no speci speci f i c data data has has bee been n pr pr ovi ovi ded ded f or t he engi engi ne f uel uel consum consumpti on or or pow power vari ati on wi t h al al t i t ude, ude, so t he pr pr ogr ogr am can onl onl y make ake ver ver y gene generr al assum assumpti ons ons f or t hese hese val val ues. ues.


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Append endi x A: A: Pr ogr ogr am Out put


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** ** ** ** ** ** *

Cessna Skyha Skyhaw wk I I / 100 100 ( 172) 172) Per Per f ormance ance Check heck

** ** ** ** ** ** *

I nput nput Param Paramet ers :

Stal l speed speed wi t hout hout f l aps aps Maxi axi muml i f t coeff coeff i ci ent ent Maxi axi muml i f t coeff coeff wi t h f l aps aps Maxi axi mumt akeake- off wei ght ght Empt y wei ght ght Wi ng span Ai r p l a ne ne ef f i c i enc y f ac t o r Engi Engi ne brake hors epow epower Maxi mum l evel speed Propel Propel l or di ameter Pr o pe pel l or r p m

VS1 = 57. 57. 0 CLmax = 1. 60 CLmaxf axf = 2 2.. 10 W= 2300. 00. We = 1568 1568.. B = 35. 35. 83 E = 0. 700 BHP = 160. 160. Vmax = 144. 144. 0 Dp = 75. 0 RPM = 2700.

mph

lb lb ft HP mph i nche nches s rpm

The The engi engi ne i s n norm ormal l y aspi aspi r ated F i x ed ed- pi t c h pr o pe pel l or f i t t ed t o ai r c r a f t Number ber of propel propel l ors = 1 A Ave verr age age r ange ange propul propul si ve ef f i ci ency ency = 0. 700 Aver ver age age endu endurr ance ance propul propul si ve eff i ci ency ency = 0. 700 Ai r c r a f t pr o pu pul s i v e ef f i c i e nc nc y = 0. 0. 750


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** ** ** ** ** ** *


** ** ** ** ** ** *

Output utput Quanti uanti t i es :

Wi ng l oadi oadi ng Stal l speed speed wi t h f l aps aps Wi ng area Aspect spect r ati o Chor hor d Ef f ect ect i ve aspec aspectt rat i o Ef f ect ect i ve span span Ef f ect ect i ve chord chord Ef f ect ect i ve span span l oad oadi ng Dr ag area Zer o - l i f t dr a g c oe oef f i c i ent

W/ S Vs0 S AR C ARe Be Ce W/ Be AD Cd0

= 13. 3 = 49. 8 = 173. 173. 0 = 7. 42 = 4. 83 = 5. 20 = 29. 98 = 5. 77 = 76. 72 = 5. 89 = 0. 0341

l b/f t 2 mph ft2 ft ft ft l b/ f t ft2

Ai r speed speed f or mi ni mum si nk Vmi ns = 63. 63. 5 mph Mi ni mumpower r equi equi r ed f or l evel evel f l i ght ght THPm= 41. 06 HP Mi ni mum drag Dmi n = 210. 210. 1 l b Mi ni mum si nk r ate RSmi n = 589. 589. 1 f pm Maxi axi muml i f t - t o-dr ag r ati o LDm LDmax = 10. 94 Li f t coeff coeff i ci ent ent at mi ni mum si nk CLmi ns = 1. 29 Maxi axi mumi deal deal cl i mb r ate RCst ar = 2295. 7 f pm Ref erence prop ai r speed speed f or . 74 ef f Vprop = 67. 67. 0 mph I deal i z ed ed s t a t i c t h r u s t Ts = 1041. 0 l b Pr opel opel l or t i p Mach number Mp = 0. 7915 7915


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*** *** *** *** *

Cessna Skyh Skyhaw awk I I / 100 100 ( 172) 172) Per Per f ormance ance Check heck

Al t i t ude ude

0. f eet eet

:

Ai r speed V( mp h) h) 5 7. 7. 0 6 0. 0. 0 70. 70. 0 80. 80. 0 90. 90. 0 100. 100. 0 110. 110. 0 120. 120. 0 130. 130. 0 1 40 40 . 0 1 50 50 . 0 1 54 54 . 0

Rat e- of - Cl i mb RC( f p m)

Ambi ent ent t emper per atur e Ambi ent pr essur e Densi ensi t y r ati o Speed Speed of sound

Si nk Rat e RS ( f p m)

4 41 41 . 4 90 90 . 613. 613. 678. 678. 689. 689. 647. 647. 551. 551. 401. 401. 195. 195. - 6 8. 8. - 3 91 91 . - 5 37 37 .

5 74 74 . 5 70 70 . 585. 585. 640. 640. 733. 733. 866. 866. 1040 1040.. 1256 1256.. 1516 1516.. 1 82 82 3. 3. 2 17 17 7. 7. 2 33 33 2. 2.

Maxi mum esti mated ai r cr af t range range i s Maxi mum est i mat ed endurance endurance i s

T ax ax i / T ak ak ee- o f f f u el el u s ed ed Cl i mb f uel uel used used Descent f uel used Landi Landi ng/ ng/ Taxi Taxi f uel uel used used Reserve f uel uel avai avai l abl abl e Tot Tot al f uel uel for cl i mb and and descen descentt F ue ue l a va va i l a bl bl e f o r c r u i s e

Range ange att ai ned ned dur dur i ng cl i mb Range ange at t ai ned duri ng descent descent

Ti me t aken dur dur i ng cl i mb Ti me t aken dur dur i ng descent descent


= =

= =

*** *** *** *** *

= 288. 288. 15 deg. deg. K = 2116. 2116. 2 psf = 1. 0000 0000 = 1116. 1116. 4 f ps

Reyn Reynol ol ds No

THP THP ( h p) p)

Thrust ( l b)

2.6 2.7 3. 2 3. 6 4. 1 4. 4. 5 5. 5. 0 5. 5. 4 5. 5. 9 6.3 6. 8 6. 9

6 8. 8. 7 1. 1. 80. 80. 88. 88. 95. 95. 101. 101. 106. 106. 111. 111. 115. 115. 1 18 18 . 1 22 22 . 1 23 23 .

4 46 46 . 4 42 42 . 427. 427. 411. 411. 394. 394. 378. 378. 362. 362. 346. 346. 331. 331. 3 17 17 . 3 04 04 . 2 99 99 .

mi l mi l mi l mi l mi l mi l mi l mi l mi l mi l mi l mi l

l l l l l l l l l l l l

i i i i i i i i i i i i

on on on on on on on on on on on on

Dr ag ( l b) 2 53 53 . 2 38 38 . 209. 209. 200. 200. 204. 204. 217. 217. 237. 237. 263. 263. 294. 294. 3 29 29 . 3 69 69 . 3 85 85 .

L/ D

SEP SEP ( f t / sec)

8.6 9.2 10. 10. 5 10. 10. 9 10. 10. 7 10. 10. 1 9. 2 8. 3 7. 4 6.6 5.9 5.7

7.4 8.2 10. 10. 2 11. 11. 3 11. 11. 5 10. 10. 8 9. 2 6. 7 3. 2 - 1.1 - 6.5 - 8.9

Mach No.

0.075 0.079 0. 092 092 0. 105 105 0. 118 118 0. 131 131 0. 145 145 0. 158 158 0. 171 171 0.184 0.197 0.202

760. 760. mi l es 4. 5 hour hour s

= = = = = = =

5.88 0. 12 0. 15 4. 20 56. 56. 70 67. 67. 05 1 56 56 . 0 1

l bs l bs l bs l bs l bs l bs l bs

0. 1 mi l es 0. 1 mi l es

0. 1 mi nut nut es 0. 1 mi nut nut es

Page 13

*** *** *** *** *

Al t i t ude ude

:

Ai r speed V( mp h) h) 5 7. 7. 0 6 0. 0. 0 7 0. 0. 0 80. 80. 0 90. 90. 0 100. 100. 0 110. 110. 0 120. 120. 0 130. 130. 0 1 40 40 . 0 1 50 50 . 0 1 54 54 . 0


5000 5000.. f eet eet




2 22 22 . 2 70 70 . 3 92 92 . 460. 460. 479. 479. 450. 450. 373. 373. 248. 248. 75. 75. - 1 48 48 . - 4 23 23 . - 5 48 48 .

6 32 32 . 6 22 22 . 6 17 17 . 650. 650. 720. 720. 826. 826. 969. 969. 1150 1150.. 1370 1370.. 1 63 63 2. 2. 1 93 93 7. 7. 2 07 07 1. 1.


T ax ax i / T ak ak ee- o f f f u el el u s ed ed Cl i mb f uel used Descent f uel used Landi Landi ng/ ng/ Taxi Taxi f uel uel used used Reserve f uel uel avai avai l abl abl e Tot Tot al f uel uel for cl i mb and and descen descentt F ue ue l a va va i l a bl bl e f o r c r u i s e

Range ange att ai ned ned dur dur i ng cl i mb Range ange at t ai ned duri ng descent descent



= =

= =

*** *** *** *** *

= 278. 278. 24 deg deg.. K = 1760. 1760. 8 psf = 0. 8617 8617 = 1097. 1097. 0 f ps


THP THP ( h p) p)

Thrust ( l b)

2.2 2.3 2.7 3. 1 3. 5 3. 9 4. 3 4. 7 5. 0 5. 4 5. 8 6. 0

5 7. 7. 6 0. 0. 6 7. 7. 74. 74. 80. 80. 85. 85. 89. 89. 93. 93. 97. 97. 1 00 00 . 1 02 02 . 1 03 03 .

3 76 76 . 3 73 73 . 3 60 60 . 346. 346. 333. 333. 319. 319. 305. 305. 292. 292. 279. 279. 2 67 67 . 2 56 56 . 2 52 52 .





Dr ag ( l b) 2 79 79 . 2 61 61 . 2 21 21 . 203. 203. 200. 200. 207. 207. 221. 221. 240. 240. 265. 265. 2 94 94 . 3 26 26 . 3 40 40 .

L/ D


7.8 8.4 9.9 10. 10. 8 10. 10. 9 10. 10. 6 9. 9 9. 1 8. 3 7.4 6.7 6.4

3.7 4.5 6.5 7. 7 8. 0 7. 5 6. 2 4. 1 1. 3 - 2.5 - 7.1 - 9.1

Mach No.

0.076 0.080 0.094 0. 107 107 0. 120 120 0. 134 134 0. 147 147 0. 160 160 0. 174 174 0.187 0.201 0.206


= = = = = = =

5.88 12. 12. 20 15. 04 4. 20 56. 56. 70 94. 94. 01 1 29 29 . 0 5


8. 9 mi l es 9. 5 mi l es

7. 3 mi nut nut es 9. 0 mi nut nut es

Page 14

*** *** *** *** *

Al t i t ude ude

:

Ai r speed V( mp h) h) 5 7. 7. 0 6 0. 0. 0 7 0. 0. 0 80. 80. 0 90. 90. 0 100. 100. 0 110. 110. 0 120. 120. 0 1 30 30 . 0 1 40 40 . 0 1 50 50 . 0 1 54 54 . 0


8000 8000.. f eet eet




9 1. 1. 1 39 39 . 2 62 62 . 333. 333. 357. 357. 336. 336. 270. 270. 160. 160. 5. - 1 97 97 . - 4 45 45 . - 5 58 58 .

6 74 74 . 6 60 60 . 6 43 43 . 663. 663. 720. 720. 810. 810. 936. 936. 1097 1097.. 1 29 29 5. 5. 1 53 53 1. 1. 1 80 80 8. 8. 1 93 93 0. 0.


T ax ax i / T ak ak ee- o f f f u el el u s ed ed Cl i mb f uel used Descent f uel used Landi Landi ng/ ng/ Taxi Taxi f uel uel used used Reserve f uel uel avai avai l abl abl e Tot Tot al fuel for cl i mb and and descen descentt F ue ue l a va va i l a bl bl e f o r c r u i s e

Range ange at t ai ned duri ng cl i mb Range ange at t ai ned duri ng descent descent



= =

= =

= = = = = = =


2.0 2.1 2.5 2. 8 3. 2 3. 5 3. 9 4. 2 4.6 5.0 5.3 5.4





*** *** *** *** *

= 272. 272. 30 deg deg.. K = 1571. 1571. 9 psf = 0. 7861 7861 = 1085. 1085. 3 f ps

THP THP ( h p) p)

Thrust ( l b)

5 1. 1. 5 4. 4. 6 0. 0. 66. 66. 72. 72. 76. 76. 80. 80. 84. 84. 8 7. 7. 9 0. 0. 9 2. 2. 9 3. 3.

3 38 38 . 3 35 35 . 3 23 23 . 311. 311. 299. 299. 286. 286. 274. 274. 262. 262. 2 51 51 . 2 40 40 . 2 30 30 . 2 26 26 .

Dr ag ( l b) 2 98 98 . 2 77 77 . 2 30 30 . 208. 208. 200. 200. 203. 203. 213. 213. 229. 229. 2 50 50 . 2 75 75 . 3 04 04 . 3 17 17 .

L/ D


7.3 7.9 9.5 10. 10. 5 10. 10. 9 10. 10. 8 10. 10. 3 9. 5 8.7 8.0 7.2 6.9

1.5 2.3 4.4 5. 6 6. 0 5. 6 4. 5 2. 7 0.1 - 3.3 - 7.4 - 9.3

Mach No.

0.077 0.081 0.095 0. 108 108 0. 122 122 0. 135 135 0. 149 149 0. 162 162 0.176 0.189 0.203 0.208


5.88 19. 19. 51 24. 06 4. 20 56. 56. 70 110. 110. 36 1 12 12 . 7 0


14. 14. 2 mi l es 15. 15. 2 mi l es

11. 11. 6 mi nut nut es 14. 14. 3 mi nut nut es

Page 15

*** *** *** *** *

Al t i t ude ude

:

Ai r speed V( mp h) h) 5 7. 7. 0 6 0. 0. 0 7 0. 0. 0 80. 80. 0 90. 90. 0 100. 100. 0 110. 110. 0 120. 120. 0 1 30 30 . 0 1 40 40 . 0 1 50 50 . 0 1 54 54 . 0


1000 10000. 0. f eet eet




3. 5 2. 2. 1 77 77 . 250. 250. 277. 277. 261. 261. 202. 202. 102. 102. - 4 2. 2. - 2 29 29 . - 4 61 61 . - 5 67 67 .

7 06 06 . 6 89 89 . 6 63 63 . 676. 676. 723. 723. 804. 804. 918. 918. 1066 1066.. 1 25 25 0. 0. 1 47 47 0. 0. 1 72 72 9. 9. 1 84 84 3. 3.






= =

= =

= = = = = = =


1.9 2.0 2.3 2. 7 3. 0 3. 3 3. 7 4. 0 4. 3 4. 4.7 5.0 5.1





*** *** *** *** *

= 268 268.. 34 deg. deg. K = 1455. 1455. 3 psf = 0. 7386 7386 = 1077. 1077. 3 f ps

THP THP ( h p) p)

Thrust ( l b)

4 8. 8. 5 0. 0. 5 6. 6. 62. 62. 67. 67. 71. 71. 75. 75. 78. 78. 8 1. 1. 8 3. 3. 8 6. 6. 8 6. 6.

3 14 14 . 3 11 11 . 3 01 01 . 289. 289. 278. 278. 266. 266. 255. 255. 244. 244. 2 33 33 . 2 23 23 . 2 14 14 . 2 10 10 .

Dr ag ( l b) 3 13 13 . 2 89 89 . 2 38 38 . 212. 212. 201. 201. 201. 201. 209. 209. 223. 223. 2 41 41 . 2 64 64 . 2 90 90 . 3 02 02 .

L/ D


7.0 7.6 9.2 10. 10. 3 10. 10. 9 10. 10. 9 10. 10. 5 9. 8 9.1 8.3 7.5 7.3

0.0 0.9 2.9 4. 2 4. 6 4. 4 3. 4 1. 7 - 0.7 - 3.8 - 7.7 - 9.4

Mach No.

0.078 0.082 0.095 0. 109 109 0. 123 123 0. 136 136 0. 150 150 0. 163 163 0.177 0.191 0.204 0.210


5.88 24. 24. 39 30. 08 4. 20 56. 56. 70 121. 121. 25 1 01 01 . 8 1


17. 17. 7 mi l es 18. 18. 9 mi l es


Page 16

*** *** *** *** *

Al t i t ude ude

:

Ai r speed V( mp h) h) 5 7. 7. 0 6 0. 0. 0 7 0. 0. 0 80. 80. 0 90. 90. 0 100. 100. 0 110. 110. 0 120. 120. 0 1 30 30 . 0 1 40 40 . 0 1 50 50 . 0 1 54 54 . 0


1200 12000. 0. f eet eet




- 8 6. 6. - 3 6. 6. 9 1. 1. 167. 167. 198. 198. 187. 187. 136. 136. 44. 44. - 8 9. 9. - 2 62 62 . - 4 78 78 . - 5 77 77 .

7 40 40 . 7 21 21 . 6 87 87 . 691. 691. 729. 729. 800. 800. 903. 903. 1039 1039.. 1 20 20 9. 9. 1 41 41 3. 3. 1 65 65 4. 4. 1 76 76 1. 1.






= =

= =

= = = = = = =


1.8 1.9 2.2 2. 5 2. 8 3. 1 3. 4 3. 7 4. 1 4. 4.4 4.7 4.8





*** *** *** *** *

= 264 264.. 38 deg. deg. K = 1345. 1345. 9 psf = 0. 6933 6933 = 1069. 1069. 4 f ps

THP THP ( h p) p)

Thrust ( l b)

4 4. 4. 4 6. 6. 5 2. 2. 57. 57. 62. 62. 66. 66. 69. 69. 72. 72. 7 5. 5. 7 7. 7. 7 9. 9. 8 0. 0.

2 91 91 . 2 88 88 . 2 79 79 . 268. 268. 257. 257. 247. 247. 236. 236. 226. 226. 2 16 16 . 2 07 07 . 1 98 98 . 1 95 95 .

Dr ag ( l b) 3 28 28 . 3 03 03 . 2 46 46 . 216. 216. 203. 203. 200. 200. 205. 205. 217. 217. 2 33 33 . 2 54 54 . 2 78 78 . 2 88 88 .

L/ D


6.7 7.2 8.9 10. 10. 1 10. 10. 8 10. 10. 9 10. 10. 7 10. 10. 1 9.4 8.6 7.9 7.6

- 1.4 - 0.6 1.5 2. 8 3. 3 3. 1 2. 3 0. 7 - 1.5 - 4.4 - 8.0 - 9.6

Mach No.

0.078 0.082 0.096 0. 110 110 0. 123 123 0. 137 137 0. 151 151 0. 165 165 0.178 0.192 0.206 0.211


5.88 29. 29. 27 36. 09 4. 20 56. 56. 70 132. 132. 14 9 0. 0. 9 2


21. 21. 3 mi l es 22. 22. 7 mi l es


Page 17

*** *** *** *** *

Al t i t ude ude

:

Ai r speed V( mp h) h) 5 7. 7. 0 6 0. 0. 0 7 0. 0. 0 8 0. 0. 0 90. 90. 0 100. 100. 0 110. 110. 0 1 20 20 . 0 1 30 30 . 0 1 40 40 . 0 1 50 50 . 0 1 54 54 . 0


1420 14200. 0. f eet eet




- 1 85 85 . - 1 34 34 . - 4. 7 5. 5. 111. 111. 106. 106. 62. 62. - 2 0. 0. - 1 40 40 . - 2 99 99 . - 4 98 98 . - 5 89 89 .

7 82 82 . 7 60 60 . 7 17 17 . 7 11 11 . 739. 739. 799. 799. 891. 891. 1 01 01 3. 3. 1 16 16 8. 8. 1 35 35 7. 7. 1 57 57 9. 9. 1 67 67 8. 8.






= =

= =

= = = = = = =


1.7 1.7 2.0 2.3 2. 6 2. 9 3. 2 3.5 3.8 4.1 4.4 4.5





*** *** *** *** *

= 260 260.. 02 deg. deg. K = 1233. 1233. 2 psf = 0. 6460 6460 = 1060. 1060. 5 f ps

THP THP ( h p) p)

Thrust ( l b)

4 1. 1. 4 2. 2. 4 8. 8. 5 3. 3. 57. 57. 60. 60. 64. 64. 6 6. 6. 6 9. 9. 7 1. 1. 7 3. 3. 7 4. 4.

2 67 67 . 2 65 65 . 2 56 56 . 2 46 46 . 236. 236. 226. 226. 217. 217. 2 07 07 . 1 98 98 . 1 90 90 . 1 82 82 . 1 79 79 .

Dr ag ( l b) 3 48 48 . 3 20 20 . 2 57 57 . 2 23 23 . 206. 206. 200. 200. 203. 203. 2 11 11 . 2 25 25 . 2 43 43 . 2 65 65 . 2 74 74 .

L/ D


6.3 6.8 8.5 9.8 10. 10. 6 10. 10. 9 10. 10. 8 10 10 . 3 9.7 9.0 8.3 8.0

- 3.1 - 2.2 - 0.1 1.3 1. 8 1. 8 1. 0 - 0.3 - 2.3 - 5.0 - 8.3 - 9.8

Mach No.

0.079 0.083 0.097 0.111 0. 124 124 0. 138 138 0. 152 152 0.166 0.180 0.194 0.207 0.213


5.88 34. 34. 63 42. 71 4. 20 56. 56. 70 144. 144. 13 7 8. 8. 9 3


25. 25. 2 mi l es 26. 26. 9 mi l es


Page 18

** ** ** ** ** ** *

Wei ght

Dat a


** ** ** ** ** ** *

:

Payl Payl oad oad Fuel Fuel l oad oad Maxi axi mumt ake-of ake-of f wei ght ght Empty wei ght ght Mean ean wei ght ght

= = = = =

Maxi mum dynami c pr ess ur e


732. 223. 2300. 00. 1345 1345.. 2188 2188..

l l l l l

bs bs bs bs bs Qmax =

53. 53. 0

psf

Page 19

Cessna 172 Design

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