Test 120 exam questions on Principles of Flight for ATPL

1 - The lift formula is: L= W L= CL 1/2 RHO V2 S L= n W L= CL 2 RHO V2 S

2 - The lift coefficient (CL) of an aeroplane in steady horizontal flight is 0.35. An increase in angle of attack of 1 degree would increase CL by 0.079. If a vertical gust instantly changes the angle of attack by 2 degrees, the load factor will be: 0.9 1.45 1.9 0.45

3 - The angle between the aeroplane longitudinal axis and the chord line is the: Angle of incidence Climb path angle Angle of attack Glide path angle

4 - When the Mach number is slowly increased in straight and level flight the first shockwaves will occur: On the lower surface of the wing. Somewhere on the fin. On the upper surface at the wing root. Somewhere on the horizontal tail.

5 - Which of the following statements about the spin is correct? An aeroplane is prone to spin when the stall starts at the wing root In the spin, airspeed continuously increases During spin recovery the ailerons should be kept in the neutral position Every aeroplane should be designed such that it can never enter a spin

6 - How does the total drag vary as speed is increased from stalling speed (VS) to maximum IAS (VNE) in a straight and level flight at constant weight? Decreasing, then increasing Increasing, then decreasing Increasing Decreasing

7 - In case the Mach trimmer fails: Try to relocate the centre-of-gravity aft. The Mach number must be limited. The aeroplane weight must be limited. The speed must be kept constant.

8 - What is the effect of an aft shift of the centre of gravity on ( 1) static longitudinal stability and( 2) the required control deflection for a given pitch change? (1) reduces (2) reduces (1) reduces (2) increases (1) increases (2) increases (1) increases (2) reduces

9 - At an aeroplane's minimum drag speed, what is the ratio between induced drag Di and parasite drag Dp? Di / Dp = It varies between aeroplane types. 2/1 1/1 1/2

10 - Which statement is correct regarding a shockwave on a lift generating wing? It reaches its highest strength when flying at the critical Mach number It moves slightly aft when an aileron is deflected downward It is located at the greatest wing thickness when the aeroplane reaches the speed of sound It moves forward when the Mach number is increased

11 - A conventional stabiliser on a stable aeroplane in a normal cruise condition: 1 - always provides negative lift.2 - contributes to the total lift of the aeroplane.3 - may stall before the wing, in icing conditions, with large flap settings, unless adequate design and/or operational precautions are taken.4 - is necessary to balance the total pitch moment of the aeroplane. Which of the following lists all the correct statements ? 2, 3 and 4 1 and 4 1 and 3 1, 3 and 4

12 - In straight and level flight, as speed is increased: The elevator and trim tab do not move. Both elevator and trim tab are deflected further downwards. The elevator is deflected further upwards and the trim tab further downwards. The elevator is deflected further downwards and the trim tab further upwards.

13 - Which statement is correct?The lift to drag ratio determines the Endurance speed Maximum rate of climb Horizontal distance in the climb up to a given altitude Horizontal glide distance from a given altitude at zero wind and zero thrust

14 - Vortex generators on the upper side of the wing surface will: Increase the critical Mach Number. Decrease the span wise flow at high Mach Numbers. Decrease the intensity of shock wave induced air separation. Increase the magnitude of the shock wave.

15 - 'Tuck under' is caused by (i) which movement of the centre of pressure of the wing and (ii) which change of the downwash angle at the location of the stabilizer. (i) aft (ii) increasing (i) forward (ii) decreasing (i) forward (ii) increasing (i) aft (ii) decreasing

16 - Bernoulli's equation can be written as:(pt = total pressure, ps = static pressure, q = dynamic pressure) Pt = ps - q Pt - q = ps Pt = q - ps Pt + ps = q

17 - A body is placed in a certain airstream. The airstream velocity increases by a factor 4. The aerodynamic drag will increase with a factor: 4 8 16 12

18 - Following a disturbance, an aeroplane oscillates about the lateral axis at a constant amplitude. The aeroplane is: Statically stable - dynamically neutral Statically unstable - dynamically neutral Statically stable - dynamically unstable Statically unstable - dynamically stable

19 - An aeroplane, being manually flown in the speed unstable region, experiences a disturbance that causes a speed reduction.If the altitude is maintained and thrust remains constant, the aeroplane speed will: Further decrease. Initially further decrease and thereafter increase. Initially increase and thereafter decrease. Increase.

20 - An aeroplane exhibits static longitudinal stability, if, when the angle of attack changes: The change in total aeroplane lift acts through the centre of gravity The resulting moment is positive The change in total aeroplane lift acts aft of the centre of gravity The change in wing lift is equal to the change in tail lift

21 - The critical Mach Number of an aeroplane can be increased by: Control deflection Vortex generators. Dihedral of the wings. Sweep back of the wings.

22 - The induced drag: Increases as the aspect ratio increases Has no relation to the lift coefficient Increases as the lift coefficient increases Increases as the magnitude of the tip vortices decreases

23 - The vane of a stall warning system with a flapper switch is activated by the change of the: Centre of pressure Centre of gravity Stagnation point Point of lowest pressure

24 - To be able to predict compressibility effects you have to determine the: Mach Number IAS TAS EAS

25 - The high lift device shown in the figure below is a:

Slotted flap Fowler flap Slot or slat Krueger flap

26 - In the transonic range lift will decrease at the shock stall due to the Attachment of the shock wave on the trailing edge of the wing. First appearance of a shock wave at the upper side of the wing. Separation of the boundary layer at the shock waves. Appearance of the bow wave.

27 - In a convergent tube with an incompressible sub-sonic airflow, the following pressure changes will occur:Ps = static pressure.Pdyn = dynamic pressure. Ptot = total pressure. Ps increases, Pdyn decreases, Ptot remains constant Ps decreases, Pdyn increases, static temperature increases Ps decreases, Pdyn increases, Ptot remains constant Ps decreases, Ptot increases, static temperature decreases

28 - If an aeroplane exhibits insufficient stick force per g, this problem can be resolved by installing: A spring which pulls the stick backwards A spring which pushes the stick forwards A bobweight in the control system which pulls the stick forwards A bobweight in the control system which pulls the stick backwards

29 - Some aeroplanes have a 'waist' or 'coke bottle' contoured fuselage. This is done to Increase the strength of the wing root junction. Apply area rule. Improve the low speed characteristics. Fit the engine intakes better to the fuselage.

30 - For a fixed-pitch propeller in flight at a given TAS, the blade angle of attack will: Remain constant if RPM increases. Decrease if RPM decreases. Remain constant if RPM decreases. Increase if RPM decreases.

31 - The difference between IAS and TAS will: Increase with decreasing temperature Increase with increasing air density Decrease with decreasing altitude Decrease with increasing speed

32 - An aeroplane has a stalling speed of 100 KT in a steady level flight. When the aeroplane is flying a level turn with a load factor of 1.5, the stalling speed is: 123 KT 150 KT 82 KT 141 KT

33 - Which design features improve static lateral stability?1. Anhedral.2. Dihedral.3. Forward sweep.4. Sweepback.The combination that regroups all of the correct statements is: 1, 4. 2, 3. 1, 3. 2, 4.

34 - If you push forward the RPM lever of a constant speed propeller during a glide with idle power and constant speed, the propeller pitch will: Increase and the rate of descent will increase. Increase and the rate of descent will decrease. Decrease and the rate of descent will decrease. Decrease and the rate of descent will increase.

35 - Critical Mach number is the free stream Mach number at which: There is subsonic flow over all parts of the aeroplane. Local supersonic flow first exists on any part of the aeroplane. The aeroplane has zero buffet margin. There is supersonic flow over all parts of the aeroplane.

36 - 'Flutter' may be caused by: Low airspeed aerodynamic wing stall. Roll control reversal. Distortion by bending and torsion of the structure causing increasing vibration in the resonance frequency. High airspeed aerodynamic wing stall.

37 - When the air has passed through a normal shock wave the Mach number is Lower than before but still greater than 1. Equal to 1. Less than 1. Higher than before.

38 - When a strongly swept back wing stalls and the wake of the wing contacts the horizontal tail, the effect on the stall behaviour can be a(n): Nose down tendency Increase in sensitivity of elevator inputs Nose up tendency and / or lack of elevator response Tendency to increase speed after initial stall

39 - Static lateral stability will be increased by: Reducing wing sweepback. Reducing the size of the vertical tail. Reducing wing anhedral. The use of a low, rather than high, wing mounting.

40 - The CG of an aeroplane is in a fixed position forward of the neutral point. Which of these statements about the stick force stability is correct? Maintaining a steady speed above the trim speed requires a pull force An increase of 10 KT from the trimmed position at low speed has more effect on the stick force than an increase of 10 KT from the trimmed position at high speed Stick force stability is not affected by trim Aeroplane nose up trim decreases the stick force stability

41 - Deflection of leading edge flaps will: Decrease drag Decrease CLmax Not affect critical angle of attack Increase critical angle of attack

42 - When power assisted controls are used for pitch control: Trimming is superfluous. A part of the aerodynamic forces is still felt on the column. They only function in combination with an elevator trim tab. Aerodynamic balancing of the control surfaces is meaningless.

43 - Increasing air density will have the following effect on the drag of a body in an airstream (angle of attack and TAS are constant): The drag decreases This has no effect The drag is only affected by the ground speed The drag increases

44 - Which of the following situations leads to a decreasing stall speed (IAS)? Increasing air density Increasing altitude Increasing load factor Decreasing weight

45 - Mach buffet occurs: At the Mach Number at which shockwave induced boundary layer separation occurs. When the stalling angle of attack is exceeded. Directly after exceeding Mcrit. When the Mach Number has increased to Mcrit.

46 - What is the approximate value of the lift of an aeroplane at a gross weight of 50000 N, in a horizontal coordinated 45 degrees banked turn? 60000 N 50000 N 70000 N 80000 N

47 - Which statement is correct for a side slip condition at constant speed and side slip angle, where the geometric dihedral of an aeroplane is increased ? The required lateral control force does not change. The required lateral control force decreases. The stick force per g decreases. The required lateral control force increases.

48 - During landing of a low-winged jet aeroplane, the greatest elevator up deflection is normally required when the flaps are: Fully down and the cg is fully aft. Up and the cg is fully forward. Up and the cg is fully aft. Fully down and the cg is fully forward.

49 - When air has passed through a shock wave the local speed of sound is: Not affected Decreased Increased Decreased and beyond a certain Mach number start increasing again

50 - Which of the following ( 1) aerofoils and ( 2) angles of attack will produce the lowest Mcrit values? (1) thin and (2) large. (1) thick and (2) small. (1) thin and (2) small. (1) thick and (2) large.

51 - In straight and level flight, as speed is reduced: Both elevator and trim tab are deflected further upwards. The elevator is deflected further upwards and the trim tab further downwards. The elevator is deflected further downwards and the trim tab further upwards. The elevator and trim tab do not move.

52 - VLE is defined as the: Maximum flap extended speed. Maximum speed at which the landing gear may be extended or retracted. Maximum authorised speed. Maximum landing gear extended speed.

53 - The critical Mach number for an aerofoil equals the free stream airfoil Mach number at which: The maximum operating temperature is reached. A shock-wave appears on the upper surface. Sonic speed (M=1) is reached at a certain point on the upper side of the aerofoil. A 'supersonic bell' appears on the upper surface.

54 - The value of the manoeuvre stability of an aeroplane is 150 N / g. The stick force required to achieve a load factor of 2.5 from steady level flight is: 225 N 150 N 450 N 375 N

55 - Rotation around the normal axis is called: Rolling. Slipping. Pitching. Yawing.

56 - Compared with an oblique shock wave at the same Mach number a normal shock wave has a Higher total pressure. Higher total temperature. Higher loss in total pressure. Lower static temperature.

57 - The relationship between the stall speed VS and VA (EAS) for a large transport aeroplane can be expressed in the following formula:(SQRT= square root) VA <= VS SQRT(2.5) VA > VS SQRT(2.5) VA < VS SQRT(2.5) VA >= VS SQRT(2.5)

58 - What is the effect of high aspect ratio of an aeroplane's wing on induced drag? It is increased because high aspect ratio has greater frontal area It is reduced because the effect of wing-tip vortices is reduced It is increased because high aspect ratio produces greater downwash It is unaffected because there is no relation between aspect ratio and induced drag

59 - The maximum acceptable cruising altitude is limited by a minimum acceptable loadfactor because exceeding that altitude: Turbulence may exceed the limit load factor. Turbulence may induce Mach buffet. Mach buffet will occur immediately. A sudden necessary bankangle may exceed the limit load factor.

60 - The critical Mach Number of an aeroplane is the free stream Mach Number, which produces the first evidence of: Shock wave. Buffet. Supersonic flow. Local sonic flow.

61 - If in a two-dimensional incompressible and subsonic flow, the streamlines converge the static pressure in the flow will: Decrease Increase initially, then decrease Not change Increase

62 - The regime of flight from the critical Mach number up to approximately M = 1.3 is called the: Supersonic range Transonic range Subsonic range Hypersonic range

63 - A jet aeroplane cruises buffet free at high constant altitude. Which type of stall can occur if this aeroplane decelerates during an inadvertent increase in load factor? Low speed stall Accelerated stall Deep stall Shock stall

64 - The pitch up effect of an aeroplane with swept wing in a stall is due to the Wing tip stalling first Wing root stalling first Forward movement of the centre of gravity Aft movement of the centre of gravity

65 - In what flight phase are the outboard ailerons (if present) not operated ? During cruise flight. During a landing with strong and gusty crosswind to avoid overcontrolling the aeroplane. In the approach phase, before landing. During take-off, until lift-off.

66 - The effects of very heavy rain (tropical rain) on the aerodynamic characteristics of an aeroplane are: Decrease of CLmax and decrease of drag Decrease of CLmax and increase of drag Increase of CLmax and decrease of drag Increase of CLmax and increase of drag

67 - On a symmetrical aerofoil, the pitching moment for which CL = 0 is: Equal to the moment coefficient for stabilized angle of attack Zero Negative (pitch-down) Positive (pitch-up)

68 - One method to compensate adverse yaw is: A differential aileron. A balance panel. An anti-balance tab. A balance tab.

69 - What is the position of the elevator in relation to the trimmable horizontal stabiliser of a power assisted aeroplane that is in trim? The elevator deflection (compared to the stabilizer position) is always zero. At a forward CG the elevator is deflected upward and at an aft CG the elevator is deflected downward. The position depends on speed, the position of slats and flaps and the position of the centre of gravity. The elevator is always deflected slightly downwards in order to have sufficient remaining flare capability.

70 - Assuming ISA conditions, climbing at a constant Mach Number up to FL 350 the TAS will: Increase First increase, then decrease Remain constant Decrease

71 - Two identical aircraft A and B, with the same mass, are flying steady level co-ordinated 20 degree bank turns. If the TAS of A is 130 KT and that of B is 200 KT: The rate of turn of A is greater than that of B The lift coefficient of A is less than that of B The turn radius of A is greater than that of B The load factor of A is greater than that of B

72 - The value of the induced drag of an aeroplane in straight and level flight at constant weight varies linearly with: V2 1/V2 1/V V

73 - In case of supersonic flow retarded by a normal shock wave a high efficiency (low loss in total pressure) can be obtained if the Mach number in front of the shock is Lower than 1. High (supersonic). Exactly 1. Small but still supersonic.

74 - What data may be obtained from the Buffet Onset Boundary chart? The values of Mcrit at different weights and altitudes The values of MMO at different weights and altitudes The values of the Mach Number at which low speed and shock-stall occur at different weights and altitudes The values of the Mach Number at which low speed and Mach Buffet occur at different weights and altitudes

75 - An aeroplane, with a C.G. location behind the centre of pressure of the wing can only maintain a straight and level flight when the horizontal tail loading is: Zero. Downwards. G. location behind the centre of pressure of the wing can only maintain a straight and level flight when the horizontal tail loading is: zero. downwards. upwards. Upwards or downwards depending on elevator deflection.

76 - In which phase of the take-off is the aerodynamic effect of ice located on the wing leading edge most critical? The last part of the rotation All phases of the take-off are equally critical During climb with all engines operating The take-off run

77 - During an erect spin recovery: The control stick is moved side ways, against the angle of bank The ailerons are held in the neutral position The control stick is pulled to the most aft position The control stick is moved side ways, in the direction of the angle of bank

78 - A body is placed in a certain airstream. The density of the airstream decreases to half of the original value. The aerodynamic drag will decrease with a factor: 8 4 1.4 2

79 - With increasing angle of attack, the stagnation point will move (I) ...and the point of lowest pressure will move (II) ...Respectively (I) and (II) are: (I) down, (II) forward. (I) up, (II) forward. (I) down, (II) aft. (I) up, (II) aft.

80 - During initiation of a turn with speedbrakes extended, the roll spoiler function induces a spoiler deflection: Upward on the upgoing wing and downward on the downgoing wing. Downward on the upgoing wing and upward on the downgoing wing. On the downgoing wing only. On the upgoing wing only.

81 - What wing shape or wing characteristic is the least sensitive to turbulence: Swept wings Elliptical wing Wing dihedral Straight wings

82 - Constant-speed propellers provide a better performance than fixed-pitch propellers because they: Produce a greater maximum thrust than a fixed-pitch propeller. Have a higher maximum efficiency than a fixed-pitch propeller. Have more blade surface area than a fixed-pitch propeller. Produce an almost maximum efficiency over a wider speed range.

83 - The high lift device shown in the figure is a:

Slat Krueger flap Slotted flap Fowler flap

84 - When Fowler type trailing edge flaps are extended at a constant angle of attack, the following changes will occur: CL increases and the centre of pressure moves forward CL and CD increase CD decreases and the centre of pressure moves aft CL increases and CD remains constant

85 - When flaps are deployed at constant angle of attack the lift coefficient will: Increase Vary as the square of IAS Remain the same Decrease

86 - If flaps are deployed at constant IAS in straight and level flight, the magnitude of tip vortices will eventually: (flap span less than wing span) Increase Decrease Increase or decrease, depending on the initial angle of attack Remain the same

87 - The aeroplane drag in straight and level flight is lowest when the: Induced drag is equal to zero Parasite drag equals twice the induced drag Induced drag is lowest Parasite drag is equal to the induced drag

88 - The 'short period mode' is an: Oscillation about the lateral axis Unstable movement of the aeroplane, induced by the pilot Oscillation about the longitudinal axis Oscillation about the vertical axis

89 - One important advantage the turbulent boundary layer has over the laminar layer is that: It has less tendency to separate from the surface Energy is less Skin friction drag is less It is thinner

90 - The span-wise flow is caused by the difference between the air pressure on top and beneath the wing and its direction of movement goes from: Beneath to the top of the wing via the wing tip The top to beneath the wing via the leading edge Beneath to the top of the wing via the trailing edge The top to beneath the wing via the wing's trailing edge

91 - The flight Mach number is 0.8 and the TAS is 400 kts. The speed of sound is: 500 kts 600 kts 480 kts 320 kts

92 - An aeroplane maintains straight and level flight while the IAS is doubled. The change in lift coefficient will be: X 0.25 X 4.0 X 0.5 X 2.0

93 - The stall speed in a 60° banked turn increases by the following factor: 1.41 2.00 1.30 1.07

94 - What should be usually done to perform a landing with the stabilizer jammed in the cruise flight position ? Choose a lower landing speed than normal. If possible, relocate as many passengers as possible to the front of the cabin. Choose a higher landing speed than normal and/or use a lower flap setting for landing. Use the Mach trimmer until after landing.

95 - Which aeroplane behaviour will be corrected by a yaw damper ? Tuck under. Dutch roll. Buffeting. Spiral dive.

96 - The effect on static stability of an aeroplane with a high wing as compared to a low wing is: A negative dihedral effect A positive dihedral effect Zero dihedral effect No effect as it is only used to improve aeroplane loading

97 - After the transition point between the laminar and turbulent boundary layer The mean speed increases and the friction drag decreases The boundary layer gets thinner and the speed increases The boundary layer gets thicker and the speed decreases The mean speed and friction drag increases

98 - Which formula or equation describes the relationship between force (F), acceleration (a) and mass (m)? M=F.a A=F. m F=m. a F=m / a

99 - Which of the following statements about dihedral is correct? The 'effective dihedral' of an aeroplane component means the contribution of that component to the static lateral stability. Dihedral is necessary for the execution of slip-free turns. Dihedral contributes to dynamic but not to static lateral stability. Effective dihedral is the angle between the 1/4-chord line and the lateral axis of the aeroplane.

100 - Tick force per g is independent of altitude.II Stick force per g increases when the centre of gravity moves forward. I is correct, II is correct. I is correct, II is incorrect. I is incorrect, II is correct. I is incorrect, II is incorrect

101 - The trailing edge flaps when extended: Degrade the best angle of glide Significantly lower the drag Significantly increase the angle of attack for maximum lift Increase the zero lift angle of attack

102 - Air passes a normal shock wave. Which of the following statements is correct? The static temperature increases The velocity increases The static temperature decreases The static pressure decreases

103 - The diagram shows the parameter X versus TAS. If a horizontal flight is considered the axis X shows

The induced drag The parasite drag The lift force The total drag

104 - During the extension of the flaps at a constant angle of attack the aeroplane starts to (all other factors of importance being constant) Bank. Climb. Yaw. Sink suddenly.

105 - The correct drag formula is: D = CD 1/2 RHO V S D = CD 2 RHO V2 S D = CD 1/2 1/RHO V2 S D = CD 1/2 RHO V2 S

106 - The Mach number: Is the ratio between the TAS of the aeroplane and the speed of sound at sea level. Is the ratio between the IAS of the aeroplane and the local speed of sound. Is the ratio between the TAS of the aeroplane and the local speed of sound. Increases at a given TAS, when the temperature rises.

107 - VA is: The maximum speed at which rolls are allowed. The speed at which a heavy transport aeroplane should fly in turbulence. The maximum speed at which maximum elevator deflection up is allowed. The speed that should not be exceeded in the climb.

108 - When an aeroplane with the centre of gravity forward of the centre of pressure of the combined wing / fuselage is in straight and level flight, the vertical load on the tailplane will be: Zero because in steady flight all loads are in equilibrium. Upwards. Downwards because it is always negative regardless of the position of the centre of gravity. Downwards.

109 - The angle of attack of a two dimensional wing section is the angle between: The chord line of the aerofoil and the fuselage centreline The chord line of the aerofoil and the free stream direction The chord line and the camber line of the aerofoil The fuselage centreline and the free stream direction

110 - On a wing fitted with a 'Fowler' type trailing edge flap, the 'Full extended' position will produce: An unaffected wing area and increase in camber An increase in wing area and camber An increase in wing area only An unaffected CD, at a given angle of attack

111 - The stalling speed in IAS will change according to the following factors: Decrease in a forward c.g. location, higher altitude and due to the slip stream from a propeller on an engine located forward of the wing Increase during turn, increased mass and forward c.g. location Increase with increased load factor, more flaps but will not increase due to the bank angle in a turn Increase with increased load factor, icing conditions and an aft c.g. location

112 - The lift formula is: (rho = density) L = CL 1/2rho V2 S L = n W L = CL 2rho V2 S L = W

113 - An example of differential aileron deflection during initiation of left turn is: Left aileron: 2° u 34. An example of differential aileron deflection during initiation of left turn is: Left aileron: 2° u 34. An example of differential aileron deflection during initiation of left turn is: Left aileron: 2° u 34. An example of differential aileron deflection during initiation of left turn is: Left aileron: 2° up

114 - If you increase the propeller pitch during a glide with idle-power at constant IAS the lift to drag ratio will Decrease and the rate of descent will decrease. Increase and the rate of descent will increase. Decrease and the rate of descent will increase. Increase and the rate of descent will decrease.

115 - Which of the following wing planforms produces the lowest induced drag? (all other relevant factors constant) Tapered Rectangular Circular Elliptical

116 - Which statement about stick force per g is correct? The stick force per g increases, when centre of gravity is moved aft. The stick force per g must have both an upper and lower limit in order to ensure 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 case of an unacceptable value.

117 - The aerodynamic centre of the wing is the point, where: Changes of lift due to variations in angle of attack are constant. Aerodynamic forces are constant. The pitching moment coefficient does not vary with angle of attack. The aeroplane's lateral axis intersects with the centre of gravity.

118 - Load factor is: Lift/Weight Wing loading 1/Bank angle Weight/Lift

119 - The extreme right limitation for both V-n (gust and manoeuvre) diagrams is created by the speed: Vflutter VC VMO VD

120 - Winglets Decrease the static lateral stability Increase the manoeuvrability Decrease the induced drag Create an elliptical lift distribution

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