Principles of Flight Questions QBDescripción completa
Principles of Flight Questions QB
ATPL POF - Principles of Flight. Easy to go and studyDescrição completa
principle of flight ppl study guideFull description
principle of flight ppl study guide
principle of flight ppl study guideFull description
Exam Practice Questions on Advanced Management Accounting Sample Questions for Final Exam : WITH SOLUTIONS
Practice exam for CSWA-CSWPDescripción completa
Practice Paper 5
44 Questions NAME ____________________ 1. Which of the following flight phenomena phenomena can happen at Mach Numbers below the critical Mach Number? A.
Mach buffet.
B.
Shock stall.
C.
Tuck under.
.
utch roll.
!.
The speed of sound is affected b" the?
A.
densit" of the air.
B.
temperature of the air.
C.
humidit" of the air.
.
pressure of the air.
#.
$%tension of &'W($) trailing edge flaps causes?
A.
no change in pitching moment.
B.
a nose*up pitching moment.
C.
a reduction in drag.
.
a nose*down pitchi pitching ng moment.
4.
The following unit of measurement+ kgm,s- is e%pressed in the S*s"stem as?
A.
/ascal
B.
Newton
C.
0oule
.
Watt
. An aeroplane is in a stead" turn2 at a constant TAS of #33 kt2 and a bank angle of 44. ts turning radius is e5ual to? 67se g 8 13m,s s5uared9 A.
:333 metres.
B.
474#
metres.
C.
!#;1 metres.
.
##4 metres.
<. When the trailing edge flaps are deflected in le=el flight2 the change in pitch moment will be? A.
nose up.
B.
>ero.
C.
dependent on c.g. location.
.
nose down.
7.
When the air is passing through a shock wa=e the densit" will?
A.
decrease.
B.
increase.
C.
sta" constant.
.
decrease and be"ond a certain Mach number start increasing again
;.
The regime of flight from the critical Mach number up to M 8 1.# is called the?
A.
transonic range.
B.
h"personic range.
C.
subsonic range.
.
supersonic range.
:.
Which of the following statements is correct?
A. "namic stabilit" is possible onl" when the aeroplane is staticall" stable about the rele=ant a%is. B.
A d"namicall" stable aeroplane would be almost impossible to fl" manuall".
C. "namic stabilit" means that after being displaced from original e5uilibrium condition2 the aeroplane will return to that condition without oscillation. . Static stabilit" means that the aeroplane is also d"namicall" stable about the rele=ant a%is.
13. 'n an as"mmetrical2 single cur=e aerofoil2 in subsonic airflow2 at low angle of attack2 when the angle of attack is increased2 the centre of p ressure will? 6assume a con=entional transport aeroplane9 A.
mo=e forward.
B.
remain unaffected.
C.
mo=e aft.
.
remain matching the airfoil aerod"namic centre.
11. Which part of an aeroplane pro=ides the greatest positi=e contribution to the static longitudinal stabilit"? A.
The fuselage.
B.
The hori>ontal tailplane.
C.
The wing.
.
The engine.
1!.
nterference drag is the result of?
A.
the addition of induced and parasite drag.
B.
aerod"namic interaction between aeroplane parts 6e.g. wing,fuselage9.
C.
ownwash behind the wing.
.
separation of the induced =orte%.
1#.
Which statement with respect to the speed of sound is correct?
A.
oubles if the temperature increases from :4 to #<4 Centigrade.
B.
ncreases alwa"s if the densit" of the air decreases.
C.
aries with the s5uare root of the absolute temperature.
.
s independent of altitude.
14 . 'n a non swept wing2 when the aerofoil is accelerated from subsonic to supersonic speeds2 the aerod"namic centre? A.
slightl" shifts forward.
B.
remains unchanged.
C.
shifts aft b" about 13@.
.
shifts from !@ to about 3@ of the aerofoil chord.
1.
The boundar" la"er of a wing is?
A. a la"er on the wing in which the stream =elocit" is lower than the free stream =elocit". B.
created b" the normal shock wa=e at transonic speeds.
C.
a turbulent flow around the wing.
.
caused b" suction on the upper wing surface.
1<.
ihedral of the wing is?
A.
the angle between the 3.! chord line of the wing and the hori>on.
B.
the angle between the leading edge of the wing and the lateral a%is.
C.
the angle between the 3.! chord line of the wing and the =ertical a%is.
.
the angle between the 3.! chord line of the wing and the lateral a%is.
17 . Which of the following factors will cause an increase in stall speed? 6all other factors of importance being constant9 A.
/ulling out of a di=e.
B.
ecreasing weight.
C.
Minor changes in changes e.g. 3 to 13.333 ft.
.
)etracting spoilers.
1;.
The units of the densit" of the air 69 and the force 69 are+
A.
69 kg , m#2 69 N.
B.
69 N , kg2 69 kg.
C.
69 N , m#2 69 N.
.
69 kg , m-2 69 kg.
1:. uring landing of a low*winged et aeroplane2 the ma%imum ele=ator up deflection is normall" re5uired when the flaps are? A.
full" down and the C.. is full" aft.
B.
full" down and the C.. is full" forward.
C.
up and the C.. is full" aft.
.
up and the C.. is full" forward.
!3. &or a gi=en aeroplane which two main =ariables determine the =alue of MC? A.
Airport ele=ation and temperature.
B.
$ngine thrust and rudder deflection.
C.
Air densit" and runwa" length.
.
$ngine thrust and gear position.
!1. Which of the following wing planforms produces the lowest induced drag? 6all other rele=ant factors constant9 A.
Tapered.
B.
$lliptical.
C.
Circular.
.
)ectangular.
!!.
The Mach number?
A. is the ratio between the TAS of the aeroplane and the speed of sound at sea le=el. B.
is the ratio between the TAS of the aeroplane and the local speed of sound.
C.
increases at a gi=en TAS2 when the temperature rises.
.
is the ratio between the AS of the aeroplane and the local speed of sound.
!#. The location of the centre of pressure of a positi=e cambered wing at increasing angle of attack will? A.
shift aft.
B.
shift in spanwise direction.
C.
not shift.
.
shift forward.
!4 . Constant*speed propellers pro=ide a better performance than fi%ed*pitch propellers because the"? A.
produce an almost ma%imum efficienc" o=er a wider speed range.
B.
ha=e more blade surface area than a fi%ed*pitch propeller.
C.
produce a greater ma%imum thrust than a fi%ed*pitch propeller.
.
ha=e a higher ma%imum efficienc" than a fi%ed*pitch propeller.
!. A flat plate2 when positioned in the airflow at a small angle of attack2 will produce? A.
neither lift nor drag.
B.
both lift and drag.
C.
lift but no drag.
.
drag but no lift.
!<. 6&or this 5uestion use the attached anne% 3;1*
&owler flap
B.
/lain flap
C.
Split flap
.
ouble slotted flap
!7 . 0ust abo=e the critical Mach number the first e=idence of a shock wa=e will appear at the? A.
lower side of the wing.
B.
upper side of the wing.
C.
leading edge of the wing.
.
trailing edge of the wing.
!;.
ow is stall warning presented to the pilots of a large transport aeroplane?
A.
Stick shaker and,or aerod"namic buffet.
B.
Stick pusher.
C.
Stall warning light onl".
.
Aural warning onl".
!:. n case of supersonic flow retarded b" a normal shock wa=e a high efficienc" 6low loss in total pressure9 can be obtained if the Mach number in front of t he shock is? A.
small but still supersonic.
B.
high 6supersonic9.
C.
lower than 1.
.
e%actl" 1.
#3.
Minimum drag of an aeroplane in straight and le=el flight occurs at the?
A.
minimum speed.
B.
minimum C =alue.
C.
minimum angle of attack.
.
ma%imum C(*C ratio.
#1.
The stall speed?
A.
increases with the length of the wingspan
B.
increases with an increased weight
C.
decreases with an increased weight
.
does not depend on weight
#!. A et transport aeroplane e%hibits pitch up when thrust is suddenl" increased from an e5uilibrium condition2 because the thrust line is below the? A.
drag line of action.
B.
neutral point.
C.
centre of pressure.
.
C.
##.
Which of the following increase the static lateral stabilit" of an aeroplane?
A.
igh wing2 sweep back2 large and high =ertical fin.
B.
&uselage mounted engines2 dihedral2 T*tail.
C.
Sweep back2 under wing mounted engines2 winglets.
.
(ow wing2 dihedral2 elliptical wing planform.
#4 .
The units of wing loading 69 W , S and 69 d"namic pressure 5 are?
A.
69 N , m#2 69 kg , m-.
B.
69 kg , m2 69 N , m-.
C.
69 N , m2 69 kg.
.
69 N , m-2 69 N , m-.
#.
A horn balance in a control s"stem has the following purpose?
A.
to decrease stick forces.
B.
to obtain mass balancing.
C.
to decrease the effecti=e longitudinal dihedral of the aeroplane.
.
to pre=ent flutter.
#<.
The aeroplane drag in straight and le=el flight is lowest when the?
A.
parasite drag e5uals twice the induced drag.
B.
induced drag is e5ual to >ero.
C.
induced drag is lowest.
.
parasite drag is e5ual to the induced drag.
#7 . Which kind of boundar" la"er has the strongest change in =elocit" close to the surface? A.
Turbulent boundar" la"er
B.
No difference
C.
Transition boundar" la"er
.
(aminar boundar" la"er
#;.
The unit of measurement of pressure is?
A.
kg,mD
B.
lb,gal
C.
kg,dm-
.
psi
#:.
The induced drag?
A.
increases as the lift coefficient increases.
B.
increases as the magnitude of the tip =ortices decreases.
C.
increases as the aspect ratio increases.
.
has no relation to the lift coefficient.
43.
When the air is passing through an e%pansion wa=e the static temperature
will? A.
decrease and be"ond a certain Mach number start increasing again.
B.
increase.
C.
decrease.
.
sta" constant.
41.
As supersonic airflow passes through an e%pansion wa=e?
1* The densit" in front of an e%pansion wa=e is higher than behind it. !* The static pressure in f ront of an e%pansion wa=e is higher than behind it. A.
Both 1 and ! are correct.
B.
Both 1 and ! are incorrect.
C.
1 is correct and ! is incorrect.
.
1 is incorrect and ! is correct.
4!.
The Eshort period modeE is an?
A.
oscillation about the lateral a%is.
B.
oscillation about the longitudinal a%is.
C.
unstable mo=ement of the aeroplane2 induced b" the pilot.
.
oscillation about the =ertical a%is.
4#.
The lift of an aeroplane of weight W in a constant linear climb with a climb angle 6gamma9 is appro%imatel"? A.
W,cos.gamma.
B.
W61*sin.gamma9.
C.
W61*tan.gamma9.
.
Wcos.gamma.
44 .
&or a propeller that rotates clockwise when =iewed from the rear2 g"roscopic precession will cause+ . i /itch down will cause "aw to the left. ii (eft "aw will cause pitch up. . Which of the abo=e statement are correct? A.
