REVISION QUESTIONS – Air – DGCA Question Bank For Politics

#1. A unit of measurement of pressure is:

kg/square dm

kg/cubic metre

Newtons

psi

#2. Which of the following are the correct SI units ?

Density is kilogram’s per cubic metre, Force is Newtons

Density is Newton’s per cubic metre, Force is kilogram’s

Density is kilogram’s per Newton, Force is Newton-metre squared

Density is kilogram’s per square metre, Force is kilogram’s

#3. What is the SI unit of density?

m V squared

kg/square cm

kg - metres

kg/cubic metre

#4. What is the SI unit which results from multiplying kg and m/s squared?

Newton

Psi

Joule

Watt

#5. Which of the following expressions is correct:

A = F x M

F = M x A

M = F x A

A = M / F

#6. Which of the following is the equation for power?

N/m

Nm/s

Pa/s squared

Kg/m/s squared

#7. At a constant CAS when flying below sea level an aircraft will have:

a higher TAS than at sea level

a lower TAS than at sea level at ISA conditions

the same TAS as at sea level

the same TAS, but an increased IAS

#8. Static pressure acts:

parallel to airflow

parallel to dynamic pressure

in all directions

downwards

#9. TAS is:

higher than speed of the undisturbed airstream around the aircraft

lower than speed of the undisturbed airstream around the aircraft

lower than IAS at ISA altitudes below sea level

equal to IAS, multiplied by air density at sea level

#10. The difference between IAS and TAS will:

increase with decreasing temperature

increase with increasing density

remain constant at all times

decrease with decreasing altitude

#11. As a smooth flow of subsonic air at a velocity less than M0.4 flows through a divergent duct: (i) static pressure (ii) velocity

(i) increases and (ii) decreases

(i) increases and (ii) increases

(i) decreases and (ii) decreases

(i) decreases and (ii) increases

#12. As subsonic air flows through a convergent duct: (i) static pressure (ii) velocity

(i) increases and (ii) decreases

(i) increases and (ii) increases

(i) decreases and (ii) decreases

(i) decreases and (ii) increases

#13. Bernoulli’s Theorem states:

dynamic pressure increase and static pressure increase

dynamic pressure increase and static pressure decrease

dynamic pressure is maximum at stagnation point

zero pressure at zero dynamic pressure

#14. Consider a uniform flow of air at velocity V in a Streamtube. If the temperature of the air in the tube is raised:

the mass flow remains constant and velocity V decreases

the mass flow will increase and velocity V remain constant

the mass flow will decrease and velocity V will remain constant

the mass flow remains constant and the velocity V will increase

#15. In a subsonic flow venturi, the relationship between the total pressure, static pressure and dynamic pressure of undisturbed air and air in the throat will be: (i) Dynamic pressure will be constant, static pressure will decrease. (ii) Total pressure will be constant, dynamic pressure will increase.

both (i) and (ii) are correct

(i) is correct and (ii) is incorrect

(i) is incorrect and (ii) is correct

both (i) and (ii) are incorrect

#16. In accordance with Bernoulli’s Theorem, where PT = Total Pressure, PS = Static pressure and q = Dynamic pressure:

PT + PS = q

PT = PS - q

PT - PS = q

PS + PT = q

#17. The Principle of Continuity states that in a Streamtube of decreasing cross-sectional area, the speed of a subsonic and incompressible airflow will:

remain the same

decrease

increase

sonic

#18. The Principle of Continuity states that in a tube of increasing cross-sectional area, the speed of a subsonic and incompressible airflow will:

remain the same

decrease

sonic

increase

#19. What are the units for wing loading and dynamic pressure?

N/square metre and N/square metre

Nm and Nm

N and N/square metre

N/square metre and joules

#20. When considering the Principle of Continuity for incompressible subsonic flow, what happens in a Streamtube with a change in cross-sectional area?

The density at the throat will be the less than the density at the mouth

The density at the throat will be the same as the density at the mouth

The density at the throat will be greater than the density at the mouth

Cannot say without knowing the change in cross-sectional area of the Streamtube

#21. When considering the Principle of Continuity for subsonic flow, what happens in a streamtube for a change in cross-sectional area?

RHO 1 = RHO 2

RHO 1 > RHO 2

RHO 2 > RHO 1

Cannot say without knowing the change in cross-sectional area of the streamtube

#22. Which of the following creates Lift?

An accelerated air mass.

A retarded air mass.

A change in direction of mass flow

A symmetrical aerofoil at zero angle of attack in a high speed flow

#23. Which of the following statements about a venturi in a subsonic air flow is correct? (i) The dynamic pressure in the undisturbed flow and in the throat are equal. (ii) The total pressure in the undisturbed flow and in the throat are equal.

(i) is correct and (ii) is incorrect.

(i) is incorrect and (ii) is correct.

(i) and (ii) are correct

(i) and (ii) are incorrect

#24. A line from the centre of curvature of the leading edge to the trailing edge, equidistant from the top and bottom wing surface is the:

camber line

upper camber line

mean chord

mean aerodynamic chord

#25. A symmetrical aerofoil section at CL = 0 will produce?

A negative (nose down) pitching moment

A positive (nose up) pitching moment

Zero pitching moment

No aerodynamic force

#26. Angle of attack is the angle between:

undisturbed airflow and chord line

undisturbed airflow and mean camber line

local airflow and chord line

local airflow and mean camber line

#27. How is the thickness of an aerofoil section measured?

As the ratio of wing angle

Related to camber

As the percentage of chord

In metres

#28. Lift and drag respectively are normal and parallel to:

the chord line

the longitudinal axis

the horizon

the relative airflow

#29. The angle between the aeroplane longitudinal axis and the chord line is:

angle of incidence.

glide path angle.

angle of attack.

climb path angle.

#30. The term angle of attack is defined as:

the angle between the relative airflow and the horizontal axis

the angle between the wing chord line and the relative wind

the angle that determines the magnitude of the lift force

the angle between the wing and tailplane incidence

#31. What is the angle of attack (Aerodynamic angle of incidence)?

Angle of the chord line to the relative free stream flow

Angle of the chord line to the fuselage datum

Angle of the tailplane chord to the wing chord

Angle of the tailplane chord to the fuselage datum

#32. When considering the coefficient of lift and angle of attack of aerofoil sections:

a symmetrical section at zero angle of attack will produce a small positive coefficient of lift

an asymmetrical section at zero angle of attack will produce zero coefficient of lift

a symmetrical section at zero angle of attack will produce zero coefficient of lift

aerofoil section symmetry has no effect on lift coefficient

#33. When considering the Lift and Drag forces on an aerofoil section:

they are only Normal to each other at one angle of attack

they both depend on the pressure distribution on the aerofoil section

they vary linearly

Lift is proportional to Drag

#34. Where does the lift act on the wing?

Suction

Always forward of the CG

Centre of Gravity

Centre of Pressure

#35. Which of the following creates lift?

A slightly cambered aerofoil

An aerofoil in a high speed flow

Air accelerated upwards

Air accelerated downwards

#36. Which of the following is the greatest factor causing lift?

suction above the wing

increased pressure below wing

increased airflow velocity below the wing

decreased airflow velocity above the wing

#37. Which of the following statements is correct?

Lift acts perpendicular to the horizontal and drag parallel in a rearwards direction

Drag acts parallel to the chord and opposite to the direction of motion of the aircraft and lift acts perpendicular to the chord

Lift acts at right angles to the top surface of the wing and drag acts at right angles to lift

Drag acts in the same direction as the relative wind and lift perpendicular to the relative wind.

#38. With reference to Annex ‘E’, how do the speeds relate to relative wind/airflow (V)?

V1 < V2 and V2 < V

V1 = 0 and V2 = V

V1 > V2 and V2 < V

V1 = 0 and V2 > V

#39. If IAS is doubled, by which of the following factors should the original CL be multiplied to maintain level flight?

0·25

0·5

2·0

4.0

#40. On entering ground effect:

more power is required

less power is required

ground effect has no effect on power required

lift decreases

#41. On the approach to land, ground effect will begin to be felt at:

twice the wingspan above the ground

half the wingspan above the ground

when the angle of attack is increased

upon elevator deflection

#42. The formula for lift is:

L = W

L = 2 rho V squared S CL

L = 1/2 rho V squared S CL

L = rho V S CL

#43. The influence of ground affect on landing distance will:

increase landing distance

decrease landing distance

have no affect on landing distance

depend on flap position

#44. Two identical aircraft of the same weight fly at different altitudes. All other important factors remaining constant, assuming no compressibility and ISA conditions, what is the TAS of each aircraft?

The same

Greater in the higher aircraft

Greater in the lower aircraft

Less in the higher aircraft

#45. What do ‘S’ and ‘q’ represent in the lift equation?

Static pressure and chord

Wing span and dynamic pressure

Wing area and dynamic pressure

Wing area and static pressure

#46. What effect on induced drag does entering ground effect have?

Increase

Decrease

Remain the same

Induced drag will increase, but profile drag will decrease

#47. What is the CL and CD ratio at normal angles of attack

CL higher

CD higher

the same

CL much higher

#48. What is the MAC of a wing?

Area of wing divided by the span

The same as the mean chord of a rectangular wing of the same span

The mean chord of the whole aeroplane

The 25% chord of a swept wing

#49. When an aircraft enters ground effect:

the lift vector is inclined rearwards which increases the thrust required

the lift vector is inclined forwards which reduces the thrust required

the lift vector is unaffected, the cushion of air increases

the lift vector is inclined forward which increases the thrust required

#50. When an aircraft enters ground effect:

the induced angle of attack increases

lift decreases and drag increases

lift increases and drag decreases

the aircraft will be partially supported on a cushion of air

#51. When considering an angle of attack versus coefficient of lift graph for a cambered aerofoil, where does the lift curve intersect the vertical CL axis?

above the origin

below the origin

at the point of origin

to the left of the origin

#52. When in level flight at 1·3 VS, what is the CL as a percentage of CL MAX?

59%

77%

130%

169%

#53. Which of the following is the cause of wing tip vortices?

Air spilling from the top surface to the bottom surface at the wing tip

Air spilling from the bottom surface to the top surface at the wing tip

Air spilling from the bottom surface to the top surface at the left wing tip and from the top surface to the bottom surface at the right wing tip

Spanwise flow vector from the tip to the root on the bottom surface of the wing

#54. Which of the following is the correct definition of aspect ratio?

Span divided by tip chord

Chord divided by span

Span divided by mean chord

Chord divided by span, measured at the 25% chord position

#55. Which of the following most accurately describes the airflow which causes wing tip vortices?

From the root to the tip on the top surface and from the tip to the root on the bottom surface over the wing tip

From the root to the tip on the top surface and from the tip to the root on the bottom surface over the trailing edge

From the tip to the root on the top surface and from the root to the tip on the bottom surface over the trailing edge

From the tip to the root on the top surface and from the root to the tip on the bottom surface over the wing tip

#56. Which point on the curve in Annex ‘H’ represents minimum level flight speed?

A

B

C

D

#57. Wing tip vortices are caused by unequal pressure distribution on the wing which results in airflow from:

bottom to top round the trailing edge

top to bottom round the trailing edge

bottom to top round wingtip

top to bottom round wingtip

#58. With flaps deployed, at a constant IAS in straight and level flight, the magnitude of tip vortices:

increases or decreases depending upon the initial angle of attack

increases

decreases

remains the same

#59. A high aspect ratio wing:

increases induced drag

decreases induced drag

is structurally stiffer than a low aspect ratio

has a higher stall angle than a low aspect ratio

#60. An aircraft flying straight and level; if density halves, aerodynamic drag will:

increase by a factor of four

increase by a factor of two

decrease by a factor of two

decrease by a factor of four

#61. At a constant IAS, induced drag is affected by:

aircraft weight

changes in thrust

angle between chord line and longitudinal axis

wing location

#62. CDI is proportional to which of the following?

CLmax

CL squared

the square root of the CL

CL

#63. Considering the lift to drag ratio, in straight and level flight which of the following is correct?

L/D is maximum at the speed for minimum total drag

L/D maximum decreases with increasing lift

L/D is maximum when lift equals weight

L/D is maximum when lift equals zero

#64. High aspect ratio:

reduces parasite drag

reduces induced drag

increases stalling speed

increases manoeuverability

#65. How does aerodynamic drag vary when airspeed is doubled?

1

2

3

4

#66. If dynamic (kinetic) pressure increases, what is the effect on total drag (if all important factors remain constant)?

Drag decreases

Drag increases

It has no effect on drag

Drag only changes with changing ground speed

#67. If IAS is increased from 80 kt to 160 kt at a constant air density TAS will double. What would be the effect on (i) CDI and (ii) DI?

(i) 2; (ii) 2

(i) 4; (ii) 2

(i) 1/4; (ii) 4

(i) 1/16; (ii) ¼

#68. If pressure increases, with OAT and TAS constant, what happens to drag?

Increase

decrease

Remain constant

#69. If the frontal area of an object in an airstream is increased by a factor of three, by what factor does drag increase?

9

3

6

1,5

#70. If the IAS is increased by a factor of 4, by what factor would the drag increase?

4

8

12

16

#71. In a stream tube, if density is halved, drag will be reduced by a factor of:

3

2

4

6

#72. In straight and level flight, which of the following would cause induced drag to vary linearly if weight is constant?

1/V

V

1/V squared

V squared

#73. In subsonic flight, which is correct for VMD?

Parasite drag greater than induced drag

CL and CD are minimum

Parasite and Induced Drag are equal

Induced Drag is greater than Parasite Drag

#74. Induced drag can be reduced by:

increased taper ratio

decreased aspect ratio

use of a wing tip with a thinner aerofoil section

increased aspect ratio

#75. Refer to ANNEX ‘B’, which of the following is represented by vertical axis (x)?

Total drag

Induced drag

Parasite drag

Form drag

#76. The advantage of a turbulent boundary layer over a laminar boundary layer is:

decreases energy

thinner

increased skin friction

less tendency to separate

#77. The effect of Winglets is:

elliptical pressure distribution increases

reduction in induced drag

decrease in stall speed

longitudinal static stability increases

#78. What does parasite drag vary with?

Square of the speed

CLmax

Speed

Surface area

#79. What effect does aspect ratio have on induced drag?

Increased aspect ratio increases induced drag

Increased aspect ratio reduces induced drag

Changing aspect ratio has no effect

Induced drag will equal 1·3 x aspect ratio/chord ratio

#80. What happens to total drag when accelerating from CL MAX to maximum speed?

Increases

Increases then decreases

Decreases

Decreases then increases

#81. What is interference drag?

Airflow retardation over the aircraft structure due to surface irregularities

Drag caused by high total pressure at the leading edges when compared to the lower pressure present at the trailing edge

Drag caused by the generation of lift

Drag due to the interaction of individual boundary layers at the junction of aircraft major components

#82. What is the cause of induced angle of attack?

Downwash from trailing edge in the vicinity of the wing tips

Change in flow from effective angle of attack

The upward inclination of the free stream flow around the wing tips

Wing downwash altering the angle at which the airflow meets the tailplane

#83. What is the ratio of CDi ?

(CL) squared to S

(CL) squared to AR

½ rho V squared

½ rho V squared S

#84. What phenomena causes induced drag?

Wing tip vortices

Wing tanks

The increased pressure at the leading edge

The spanwise flow, inward below the wing and outward above

#85. When compared to a laminar boundary layer:

a turbulent boundary layer has more kinetic energy

a turbulent boundary layer is thinner

less skin friction is generated by a turbulent layer

a turbulent boundary layer is more likely to separate

#86. When considering the aerodynamic forces acting on an aerofoil section:

lift and drag increase linearly with an increase in angle of attack

lift and drag act normal to each other only at one angle of attack

lift and drag increase exponentially with an increase in angle of attack

lift increases linearly and drag increases exponentially with an increase in angle of attack

#87. When considering the properties of a laminar and turbulent boundary layer, which of the following statements is correct?

Friction drag is the same

Friction drag higher in laminar

Friction drag higher in turbulent

Separation point is most forward with a turbulent layer

#88. When the undercarriage is lowered in flight:

form drag will increase and the aircraft’s nose down pitching moment will be unchanged

induced drag will increase and the aircraft’s nose down pitching moment will increase

form drag will increase and the aircraft’s nose down pitching moment will increase

induced drag will decrease and the aircraft’s nose down pitching moment will increase

#89. Which of the following decreases induced drag?

Wing fences

Anhedral

Winglets

Low aspect ratio plan form

#90. Which of the following is a characteristic of laminar flow boundary layer?

Constant velocity

Constant temperature

No flow normal to the surface

No vortices

#91. Which of the following is the correct formula for drag?

½ rho V squared CL S

½ rho V (CL)squared S

½ rho V squared AR CD S

½ rho V squared CD S

#92. Which statement about induced drag and tip vortices is correct?

Vortex generators diminish tip vortices

Flow on upper and lower wing surfaces is towards the tip

They both decrease at high angle of attack

On the upper surface there is a component of flow towards the root, whilst on the lower surface it is towards the tip

#93. With reference to Annex ‘F’, which curve represents drag versus true airspeed?

(c)

(b)

(a)

(d)

#94. A jet aircraft flying at high altitude encounters severe turbulence without encountering high speed buffet. If the aircraft decelerates, what type of stall could occur first?

Low speed stall

Accelerated stall

Deep stall

Shock stall

#95. A swept wing aircraft stalls and the wake contacts the horizontal tail. What would be the stall behaviour?

nose down

nose up and/or elevator ineffectiveness

tendency to increase speed after stall

nose up

#96. An aircraft at a weight of 237402N stalls at 132 kt. At a weight of 356103N it would stall at:

88 kt

162 kt

108 kt

172 kt

#97. An aircraft at low subsonic speed will never stall:

as long as the CAS is kept above the power-on stall speed

as long as the IAS is kept above the power-on stall speed

as long as the maximum angle of attack is not exceeded

as long as the pitch angle is negative

#98. At high angle of attack, where does airflow separation begin?

Upper surface, towards the leading edge

Lower surface, towards the trailing edge

Upper surface, towards the trailing edge

Lower surface, towards the leading edge

#99. At the point of stall:

lift decreases, drag decreases

lift constant, drag increases

lift decreases, drag increases

lift decreases, drag constant

#100. During erect spin recovery the correct recovery actions are:

control stick pulled aft

ailerons held neutral

control stick sideways against bank

control stick sideways towards bank

#101. Force on the tail and its effect on VS due to CG movement:

if rearward movement of the CG gives a reduced down-force on the tail, VS will be higher

if forward movement of the CG gives a reduced down-force on the tail, VS will be higher

if rearward movement of the CG gives a reduced down-force on the tail, VS will be reduced

if rearward movement of the CG gives an increased down-force on the tail, VS will be reduced

#102. How do vortex generators work?

Re-direct spanwise flow

Take energy from free stream and introduce it into the boundary layer

Reduce kinetic energy to delay separation

Reduce the adverse pressure gradient

#103. If a jet aircraft is at 60 degrees bank angle during a constant altitude turn, the stall speed will be:

1· 60 greater

1· 19 greater

1· 41 greater

2· 00 greater

#104. If the stalling speed in a 15 degree bank turn is 60 kt, what would the stall speed be in a 45 degree bank?

83 kt

70 kt

85 kt

60 kt

#105. If the straight and level stall speed is 100 kt, what will be the stall speed in a 1·5g turn?

122 kt

150 kt

81 kt

100 kt

#106. If VS is 100 kt in straight and level flight, during a 45 bank turn VS will be:

100 kt

140 kt

81 kt

119 kt

#107. In level flight at 1.4Vs what is the approximate bank angle at which stall will occur?

44 degrees

30 degrees

60 degrees

32 degrees

#108. In recovery from a spin:

ailerons should be kept neutral

airspeed increases

ailerons used to stop the spin

rudder and ailerons used against the direction of spin rotation

#109. Stall speed in a turn is proportional to:

Lift

Weight

the square root of the load factor

TAS squared

#110. Stalling speed increases when:

recovering from a steep dive

the aircraft is subjected to minor altitude changes, i.e. 0 to 10,000 ft

the aircraft weight decreases

flaps are deployed

#111. The angle of attack at the stall:

increases with forward CG

increases with aft CG

decreases with decrease in weight

is not affected by changes in weight

#112. The CP on a swept wing aircraft will move forward due to:

boundary layer fences and spanwise flow

tip stall of the wing

flow separation at the root due to spanwise flow

change in wing angle of incidence

#113. The effect of tropical rain on drag and stall speed would be to:

increase drag and increase stall speed

increase drag and decrease stall speed

decrease drag and increase stall speed

decrease drag and decrease stall speed

#114. The IAS of a stall:

increases with high altitude; more flaps; slats

may increase with increasing altitude, especially high altitude; forward CG and icing

decreases with forward CG and increasing altitude

altitude never affects stall speed IAS

#115. Vortex generators:

take energy from the laminar flow to induce boundary layer separation

use free stream flow to induce laminar flow

prevent spanwise flow

use free stream flow to increase energy in the turbulent boundary layer

#116. VS is 100 kt at n = 1, what will the stall speed be at n = 2?

200 kt

119 kt

141 kt

100 kt

#117. What are the effects of tropical rain on: (i) CLMAX (ii) Drag

(i) increase (ii) decrease

(i) decrease (ii) increase

(i) increase (ii) increase

(i) decrease (ii) decrease

#118. What causes a swept wing aircraft to pitch-up at the stall:

Negative camber at the root

Separated airflow at the root

Spanwise flow

Rearward movement of the CP

#119. What causes deep stall in a swept back wing?

CP moves aft

CP moves forward

Root stall

Spanwise flow from tip to root on wing upper surface

#120. What does a stick pusher do?

Activate at a certain angle of attack and pull the control column backwards.

Activate at a certain angle of attack and push the stick forward.

Activate at a certain IAS and vibrate the stick.

Activate at a certain IAS and push the stick forward.

#121. What effect on stall speed do the following have?

Increased anhedral increases stall speed

Fitting a ‘T’ tail will reduce stall speed

Increasing sweepback decreases stall speed

Decreasing sweep angle decreases stall speed

#122. What happens to the stall speed with flaps down, when compared to flaps up?

Increase

Decrease

Remain the same

#123. What influence does the CG being on the forward limit have on Vs and the stall angle?

Vs increases, stall angle remains constant

Vs increases, stall angle increases

Vs decreases, stall angle remains constant

Vs decreases, stall angle decreases

#124. What is a high speed stall?

Separation of the airflow due to shockwave formation

A stall caused by increasing the load factor (g) during a manoeuvre

A stall due to decreasing CLmax at speeds above M0.4

Excessive dynamic pressure causing airflow separation

#125. What is load factor?

1 / Bank Angle

Weight / Lift

Lift / Weight

Weight / Wing area

#126. What is the percentage increase in stall speed in a 45 bank turn?

45%

41%

19%

10%

#127. What is the standard stall recovery for a light aircraft?

Pitch down, stick neutral roll, correct for bank with rudder

Pitch down, stick neutral roll, correct for bank with aileron

Pitch down, stick neutral, wait for neutral tendency

Pitch down, stick neutral roll, do not correct for bank

#128. What percentage increase in lift is required to maintain altitude while in a 45 degree bank turn?

19%

41%

50%

10%

#129. When an aircraft wing stalls:

A swept back wing will stall from the root and the CP will move aft

A non-swept rectangular wing will stall from the root and the CP will move forwards

A non-swept rectangular wing will tend to stall from the tip and the CP will move backwards

A swept back wing will stall from the tip and the CP will move forward

#130. When entering a stall, the CP of a straight rectangular wing (i) and a strongly swept wing (ii) will:

(i) move aft (ii) move forward

(i) move aft (ii) move aft

(i) move aft (ii) not move

(i) not move (ii) not move

#131. Which is the most critical phase regarding ice on a wing leading edge?

During the take off run

The last part of rotation

Climb with all engines operating

All phases are equally important

#132. Which kind of stall occurs at the lowest angle of attack?

Deep stall.

Accelerated stall.

Low speed stall.

Shock stall.

#133. Which of the following aircraft designs would be most prone to super stall?

‘T’ tail

swept forward wing

swept back wing

pod mounted engines beneath the wing

#134. Which of the following combination of characteristics would be most likely make an aircraft susceptible to deep stall?

Swept wing and wing mounted engines

Swept wing and ‘T’ tail

Straight wing and wing mounted engines

Straight wing and ‘T’ tail

#135. Which of the following is the correct designation of stall speed in the landing conFigureuration?

Vs1g

Vs1

Vso

VsL

#136. Which of the following is the most important result/problem caused by ice formation?

Increased drag

Increased weight

Blockage of the controls

Reduction in CLMAX

#137. Which of the following is the speed that would activate the stick shaker?

1.5 VS

1.15 VS

1.2 VS

Above VS

#138. Which of the following is used to activate a stall warning device?

Movement of the CP

Movement of the CG

Movement of the stagnation point

A reduction in dynamic pressure

#139. Which of the following would indicate an impending stall?

Stall strip and stick shaker

Stall strip and angle of attack indicator

Airspeed indicator and stick shaker

Stick shaker and angle of attack indicator

#140. Which stall has the greatest angle of attack?

Low speed stall

High speed stall (shock stall)

Deep stall

Accelerated stall

#141. With a swept wing the nose up phenomena is caused by:

deploying lift augmentation devices

wing fences

wing sweep prevents the nose up phenomena

tip stall

#142. When flying straight and level in 1g flight, slightly below max’ all up weight, a basic stall warning system (flapper switch) activates at 75 kt IAS and the aircraft stalls at 68 kt IAS. Under the same conditions at maximum all up weight the margin between stall warning and stall will:

increase because increasing weight increases the 1g stall speed.

decrease because the 1g stall speed is an IAS.

decrease because increasing weight increases the 1g stall speed

remain the same because increased weight increases the IAS that corresponds to a particular angle of attack.

#143. A slat on an aerofoil:

increases the energy of the boundary layer and decreases the critical angle of attack

increases the wing leading edge radius by rotating forward and down from its stowed position on the bottom side of the wing leading edge

deploys automatically under the influence of increased stagnation pressure at high angles of attack / low IAS

. increases the energy of the boundary layer and increases the maximum angle of attack

#144. After takeoff why are the slats (if installed) always retracted later than the trailing edge flaps?

Because VMCA with slats extended is more favourable compared to the flaps extended position.

Because flaps extended gives a large decrease in stall speed with relatively less drag

Because slats extended provides a better view from the cockpit than flaps extended.

Because slats extended gives a large decrease in stall speed with relatively less drag.

#145. An aircraft has trailing edge flap positions of 0, 15, 30 and 45 degrees plus slats can be deployed. What will have the greatest negative influence on CL / CD?

Deploying slats

0 - 15 flaps

15 - 30 flaps

30 - 45 flaps

#146. Extending the flaps while maintaining a constant angle of attack (all other factors constant):

the aircraft will sink suddenly

the aircraft will yaw

the aircraft will climb

the aircraft will roll

#147. For an aircraft flying straight and level at constant IAS, when flaps are deployed the induced drag:

increases

decreases

increases or decreases depending on the aircraft

stays the same

#148. How does a plain flap increase CL?

Increases camber

Increases angle of attack

Changes position of CP

Decreases the Aspect Ratio

#149. How is the pitching moment affected if flaps are deployed in straight and level flight?

Pitch up

Pitch down

Depends on CG position

#150. If flaps are extended in level flight

Lift and Drag increase

CL max increases

CL and Drag increase

CL increases

#151. If the angle of attack is maintained constant, what happens to the coefficient of lift when flaps are deployed?

Increased

Decreased

Changes with the square of IAS

Remains constant because angle of attack remains the same

#152. In order to maintain straight and level flight when trailing edge flaps are retracted, the angle of attack must:

be increased or decreased depending on type of flap

be decreased

be increased

stay the same because the lift requirement will be the same

#153. On a highly swept back wing with leading edge flaps and leading edge slats, which device would be fitted in the following possible locations?

Slats inboard, leading edge flaps outboard.

Slats outboard, leading edge flaps inboard.

Alternate leading edge flaps and slats along the wing leading edge

There is no preferred position for these two devices

#154. On a swept back wing, in which of the following locations would Krueger Flaps be fitted?

Inboard leading edge

Outboard leading edge

The leading edge

The trailing edge

#155. The effects of leading edge slats:

increase boundary layer energy, move suction peak on to slat and increase CLMAX angle of attack

increase camber, increase suction peak on main wing, increase effective angle of attack and move CLMAX to higher angle of attack

increase boundary layer energy, increase suction peak on main wing section, move CLMAX to a higher angle of attack

decrease boundary layer energy, move suction peak onto slat, move CLMAX to a lower angle of attack

#156. The illustration of ANNEX ‘C’ shows a:

plain flap

slotted flap

fowler flap

split flap

#157. The maximum angle of attack for the flaps down conFigureuration, compared to flaps up is:

greater

smaller

unchanged

smaller or greater, depending on CG position

#158. What is the effect of deploying leading edge flaps?

Decrease CLMAX

Decrease the critical angle of attack

Not affect the critical angle of attack

Increase the critical angle of attack

#159. What is the effect of deploying trailing edge flaps?

Increased minimum glide angle

Decreased minimum glide angle

Increased glide range

Decreased sink rate

#160. What is the purpose of a slat on the leading edge?

decelerate the air over the top surface

thicken the laminar boundary layer over the top surface

increase the camber of the wing

allow greater angle of attack

#161. What is true regarding deployment of Slats / Krueger flaps?

Slats increase the critical angle of attack, Krueger flaps do not

Krueger flaps increase the critical angle of attack, Slats do not

Krueger flaps form a slot, Slats do not

Slats form a slot, Krueger flaps do not

#162. What must happen to the CL when flaps are deployed while maintaining a constant IAS in straight and level flight?

increase then decrease

remain constant

decrease

increase

#163. What pitching moment will be generated when Fowler flaps are deployed on an aircraft with a high mounted (‘T’ tail) tailplane?

An aircraft nose up pitching moment

An aircraft nose down pitching moment

The nose up pitching moment will be balanced by the nose down pitching moment

The resultant aircraft pitching moment will depend upon the relative position of the CP and CG

#164. When trailing edge flaps are deployed:

a higher angle of attack is required for maximum lift.

glide distance is degraded.

CLmax decreases.

VS1g increases.

#165. Which of the following increases the stall angle?

Slats

Flaps

Spoilers

Ailerons

#166. A low wing jet aircraft is flaring to land. The greatest stick force will be experienced with:

flaps up and CG at the aft limit.

flaps fully down and Cg at the aft limit.

flaps fully down and CG at the forward limit.

flaps fully up and Cg at the forward limit.

#167. Positive static lateral stability is the tendency of an aeroplane to:

roll to the right in the case of a positive sideslip angle (aeroplane nose to the right).

roll to the left in the case of a positive sideslip angle (aeroplane nose to the left).

roll to the left in a right turn.

roll to the right in a right turn

#168. Positive static longitudinal stability means:

nose down pitching moment when encountering an up gust

nose up pitching moment with a speed change at a constant angle of attack

nose down pitching moment with a speed change at a constant angle of attack.

nose up moment when encountering an up gust.

#169. The CG of an aeroplane is in a fixed position forward of the neutral point. Speed changes cause a departure from the trimmed position. Which of the following statements about the stick force stability is correct?

An increase of 10 kt from the trimmed position at low speed has more affect on the stick force than an increase in 10 kt from the trimmed position at high speed.

Increase of speed generates pull forces.

Aeroplane nose up trim decreases the stick force stability.

Stick force stability is not affected by trim.

#170. Too much lateral static stability is undesirable because:

too much aileron needed in a cross-wind landing

too much rudder needed in a cross-wind landing

constant aileron in cruise in a cross-wind.

#171. What is the effect of an aft shift of the CG on (1) static longitudinal stability and (2) the required control deflection for a given pitch change?

(1) reduces, (2) increases

(1) increases, (2) increases.

(1) increases, (2) reduces.

(1) reduces, (2) reduces.

#172. Which statement is correct?

The stick force per ‘g’ increases when the CG is moved aft.

The stick force per ‘g’ must have both upper and lower limits in order to assure acceptable control characteristics

If the slope of the fe-n line becomes negative, generally speaking this is not a problem for control of an aeroplane.

The stick force per ‘g’ can only be corrected by means of electronic devices (stability augmentation) in the case of an unacceptable value.

#173. What is pitch angle?

The angle between the chord line and the horizontal plane.

The angle between the longitudinal axis and the horizontal plane.

The angle between the chord line and the longitudinal axis.

The angle between the relative airflow and the longitudinal axis.

#174. An aircraft of 50 tonnes mass, with two engines each of 60,000 N Thrust and with an L/D ratio of 12:1 is in a straight steady climb. Taking ‘g’ to be 10 m/s/s, what is the climb gradient?

12%

24%

15.7%

3.7%

#175. In a straight steady descent:

Lift is less than weight, load factor is equal to one

Lift is less than weight, load factor is less than one

Lift is equal to weight, load factor is equal to one

Lift is equal to weight, load factor is less than one

#176. Two aircraft of the same weight and under identical atmospheric conditions are flying level 20 degree bank turns. Aircraft ‘A’ is at 130 kt, aircraft ‘B’ is at 200 kt.

The turn radius of ‘A’ will be greater than ‘B’.

The coefficient of lift of ‘A’ will be less than ‘B’.

The load factor of ‘A’ is greater than ‘B’.

Rate of turn of ‘A’ is greater than ‘B’.

#177. VMCL can be limited by: (i) engine failure during takeoff, (ii) maximum rudder deflection.

Both (i) and (ii) are incorrect.

(i) is incorrect and (ii) is correct.

(i) is correct and (ii) is incorrect

Both (i) and (ii) are correct.

#178. Assuming ISA conditions, which statement with respect to the climb is correct?

At constant TAS the Mach number decreases.

At constant Mach number the IAS increases.

At constant IAS the TAS decreases.

At constant IAS the Mach number increases.

#179. The regime of flight from the critical Mach number (Mcrit) to approximately M1.3 is called?

Transonic.

Hypersonic.

Subsonic

Supersonic.

#180. The speed range between high and low speed buffet:

decreases during a descent at a constant Mach number.

is always positive at Mach numbers below MMO.

increases during a descent at a constant IAS.

increases during climb.

#181. When does the bow wave first appear?

At Mcrit.

At Mach 1.

Just above Mach 1.

Just below Mach 1,

#182. What can happen to the aeroplane structure flying at a speed just exceeding VA?

It may suffer permanent deformation if the elevator is fully deflected upwards.

It may break if the elevator is fully deflected upwards.

It may suffer permanent deformation because the flight is performed at to large a dynamic pressure.

It will collapse if a turn is made.

#183. Which of the following can effect VA?

Mass and pressure altitude.

Mass only.

Pressure altitude only.

It remains a constant IAS.

#184. With a vertical gust, what is the point called where the change in the vertical component of lift acts?

Neutral point.

Aerodynamic Centre.

Centre of Gravity.

Centre of Thrust.

#185. A single engine aircraft with a constant speed propeller is in a gliding descent with the engine idling, what would be the effect of decreasing the propeller pitch?

Increased L/Dmax, increased rate of descent.

Decreased L/Dmax, increased rate of descent.

Increased L/Dmax, decreased rate of descent.

Decreased L/Dmax, decreased rate of descent.

#186. The advantage of a constant speed propeller over a fixed pitch propeller is:

higher maximum thrust available

higher maximum efficiency

more blade surface area available

nearly maximum efficiency over wide speed range

#187. You are about to take-off in an aircraft with a variable pitch propeller. At brake release: (i) Blade pitch and (ii) Propeller RPM lever:

(i) reduced, (ii) increase.

(i) reduced, (ii) decrease.

(i) increased, (ii) decrease.

(i) increased, (ii) increase.

Dgca Question Bank For Pilots

Results

#1. A unit of measurement of pressure is:

#2. Which of the following are the correct SI units ?

#3. What is the SI unit of density?

#4. What is the SI unit which results from multiplying kg and m/s squared?

#5. Which of the following expressions is correct:

#6. Which of the following is the equation for power?

#7. At a constant CAS when flying below sea level an aircraft will have:

#8. Static pressure acts:

#9. TAS is:

#10. The difference between IAS and TAS will:

#11. As a smooth flow of subsonic air at a velocity less than M0.4 flows through a divergent duct: (i) static pressure (ii) velocity

#12. As subsonic air flows through a convergent duct: (i) static pressure (ii) velocity

#13. Bernoulli’s Theorem states:

#14. Consider a uniform flow of air at velocity V in a Streamtube. If the temperature of the air in the tube is raised:

#16. In accordance with Bernoulli’s Theorem, where PT = Total Pressure, PS = Static pressure and q = Dynamic pressure:

#17. The Principle of Continuity states that in a Streamtube of decreasing cross-sectional area, the speed of a subsonic and incompressible airflow will:

#18. The Principle of Continuity states that in a tube of increasing cross-sectional area, the speed of a subsonic and incompressible airflow will:

#19. What are the units for wing loading and dynamic pressure?

#20. When considering the Principle of Continuity for incompressible subsonic flow, what happens in a Streamtube with a change in cross-sectional area?

#21. When considering the Principle of Continuity for subsonic flow, what happens in a streamtube for a change in cross-sectional area?

#22. Which of the following creates Lift?

#23. Which of the following statements about a venturi in a subsonic air flow is correct? (i) The dynamic pressure in the undisturbed flow and in the throat are equal. (ii) The total pressure in the undisturbed flow and in the throat are equal.

#24. A line from the centre of curvature of the leading edge to the trailing edge, equidistant from the top and bottom wing surface is the:

#25. A symmetrical aerofoil section at CL = 0 will produce?

#26. Angle of attack is the angle between:

#27. How is the thickness of an aerofoil section measured?

#28. Lift and drag respectively are normal and parallel to:

#29. The angle between the aeroplane longitudinal axis and the chord line is:

#30. The term angle of attack is defined as:

#31. What is the angle of attack (Aerodynamic angle of incidence)?

#32. When considering the coefficient of lift and angle of attack of aerofoil sections:

#33. When considering the Lift and Drag forces on an aerofoil section:

#34. Where does the lift act on the wing?

#35. Which of the following creates lift?

#36. Which of the following is the greatest factor causing lift?

#37. Which of the following statements is correct?

#38. With reference to Annex ‘E’, how do the speeds relate to relative wind/airflow (V)?

#39. If IAS is doubled, by which of the following factors should the original CL be multiplied to maintain level flight?

#40. On entering ground effect:

#41. On the approach to land, ground effect will begin to be felt at:

#42. The formula for lift is:

#43. The influence of ground affect on landing distance will:

#44. Two identical aircraft of the same weight fly at different altitudes. All other important factors remaining constant, assuming no compressibility and ISA conditions, what is the TAS of each aircraft?

#45. What do ‘S’ and ‘q’ represent in the lift equation?

#46. What effect on induced drag does entering ground effect have?

#47. What is the CL and CD ratio at normal angles of attack

#48. What is the MAC of a wing?

#49. When an aircraft enters ground effect:

#50. When an aircraft enters ground effect:

#51. When considering an angle of attack versus coefficient of lift graph for a cambered aerofoil, where does the lift curve intersect the vertical CL axis?

#52. When in level flight at 1·3 VS, what is the CL as a percentage of CL MAX?

#53. Which of the following is the cause of wing tip vortices?

#54. Which of the following is the correct definition of aspect ratio?

#55. Which of the following most accurately describes the airflow which causes wing tip vortices?

#56. Which point on the curve in Annex ‘H’ represents minimum level flight speed?

#57. Wing tip vortices are caused by unequal pressure distribution on the wing which results in airflow from:

#58. With flaps deployed, at a constant IAS in straight and level flight, the magnitude of tip vortices:

#59. A high aspect ratio wing:

#60. An aircraft flying straight and level; if density halves, aerodynamic drag will:

#61. At a constant IAS, induced drag is affected by:

#62. CDI is proportional to which of the following?

#63. Considering the lift to drag ratio, in straight and level flight which of the following is correct?

#64. High aspect ratio:

#65. How does aerodynamic drag vary when airspeed is doubled?

#66. If dynamic (kinetic) pressure increases, what is the effect on total drag (if all important factors remain constant)?

#67. If IAS is increased from 80 kt to 160 kt at a constant air density TAS will double. What would be the effect on (i) CDI and (ii) DI?

#68. If pressure increases, with OAT and TAS constant, what happens to drag?

#69. If the frontal area of an object in an airstream is increased by a factor of three, by what factor does drag increase?

#70. If the IAS is increased by a factor of 4, by what factor would the drag increase?

#71. In a stream tube, if density is halved, drag will be reduced by a factor of:

#72. In straight and level flight, which of the following would cause induced drag to vary linearly if weight is constant?

#73. In subsonic flight, which is correct for VMD?

#74. Induced drag can be reduced by:

#75. Refer to ANNEX ‘B’, which of the following is represented by vertical axis (x)?

#76. The advantage of a turbulent boundary layer over a laminar boundary layer is:

#77. The effect of Winglets is:

#78. What does parasite drag vary with?

#79. What effect does aspect ratio have on induced drag?