Test 120 exam questions on Principles of Flight for ATPL

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1 - 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

2 - Static lateral stability should not be too small, because: The aeroplane would show too strong a tendency to spiral dive The aeroplane would show too strong a tendency for Dutch Roll The stick force per g would become unacceptably small After a disturbance around the longitudinal axis the aeroplane would show too strong a tendency to return to the original attitude

3 - Increasing dynamic pressure will have the following effect on the drag of an aeroplane (all other factors of importance remaining constant): None Drag decreases across the whole speed range At speeds greater than the minimum drag speed, drag increases Drag increases across the whole speed range

4 - When an aeroplane is flying at an airspeed which is 1.3 times its basic stalling speed, the coefficient of lift as a percentage of the maximum lift coefficient (CLmax) would be: 130% 169% 59% 77%

5 - Which part of an aeroplane provides the greatest positive contribution to the static longitudinal stability ? The fuselage. The engine. The wing. The horizontal tailplane.

6 - The aerodynamic contribution to the static longitudinal stability of the nacelles of aft fuselage mounted engines is: Zero Negative Maximum during cruise Positive

7 - 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

8 - The CL - alpha curve of a positive cambered aerofoil intersects with the vertical axis of the CL- alpha graph: Above the origin Nowhere Below the origin In the origin

9 - 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

10 - 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.

11 - An aeroplane is provided with spoilers and in- and outboard ailerons. Roll control during cruise is provided by: Outboard ailerons and roll-spoilers. Inboard and outboard ailerons. Inboard ailerons and roll-spoilers. Outboard ailerons only.

12 - VMO: Is equal to the design speed for maximum gust intensity Should be chosen in between VC and VD Should not be less than VD Should not be greater than VC

13 - 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.

14 - 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.

15 - The relative thickness of an aerofoil is expressed as: Metres Camber Degrees cross section tail angle % chord

16 - Increase of wing loading will: Increase CLmax Decrease the minimum gliding angle Decrease take off speeds Increase the stall speeds

17 - By what percentage does the lift increase in a level turn at 45° angle of bank, compared to straight and level flight? 31% 19% 52% 41%

18 - One advantage of a movable-stabilizer system compared with an elevator trim system is that: It leads to greater stability in flight The complete system (structure and control mechanism) weighs less The system's complexity is reduced It is a more effective means of trimming

19 - What is the influence of decreasing aeroplane weight on Mcrit at constant IAS ? Mcrit increases as a result of compressibility effects. Mcrit increases as a result of flying at a smaller angle of attack. Mcrit decreases as a result of flying at a greater angle of attack. Mcrit decreases.

20 - The angle of attack of a wing profile is defined as the angle between: The local airflow and the mean camberline The undisturbed airflow and the chordline The undisturbed airflow and the mean camberline The local airflow and the chordline

21 - 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.

22 - 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.

23 - The bow wave will first appear at: A Mach number just below M = 1 Mach 1 A Mach number just above M = 1 The critical Mach number

24 - 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.

25 - 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

26 - Which of the following statements about boundary layers is correct? The turbulent boundary layer has more kinetic energy than the laminar boundary layer The turbulent boundary layer will separate more easily than the laminar boundary layer The turbulent boundary layer gives a lower skin friction than the laminar boundary layer The turbulent boundary layer is thinner than the laminar boundary layer

27 - Gyroscopic precession of a propeller is induced by: Pitching and yawing. Increasing RPM and rolling. Increasing RPM and yawing. Pitching and rolling.

28 - Assuming no compressibility effects, induced drag at constant IAS is affected by: Aeroplane mass. Engine thrust. Altitude. Outside air temperature.

29 - What factors determine the distance travelled over the ground of an aeroplane in a glide ? The wind and the aeroplane's mass The wind and the lift/drag ratio, which changes with angle of attack The wind and weight together with power loading, which is the ratio of power output to the weight The wind and CLmax

30 - The lift of an aeroplane of weight W in a constant linear climb with a climb angle (gamma) is approximately: W (1-tan.gamma) W (1-sin.gamma) W / cos.gamma W cos.gamma

31 - During a phugoid the speed: Remains approximately constant, as during a short period oscillation. Varies significantly, whereas during a short period oscillation it does not. Remains approximately constant, whereas during a short period oscillation it varies significantly. Varies significantly, as during a short period oscillation.

32 - The following factors increase stall speed: Increasing bank angle, increasing thrust, slat extension A higher weight, selecting a higher flap setting, a forward CG shift A lower weight, decreasing bank angle, a smaller flap setting An increase in load factor, a forward CG shift, decrease in thrust

33 - 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.

34 - Tuck under will happen Only below the critical Mach number. Only at the critical Mach number. Above or below the critical Mach number depending on the angle of attack. Only above the critical Mach number.

35 - 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

36 - An aeroplane is flying through the transonic range. As the Mach Number increases the centre of pressure of the wing will move aft. This movement requires: A pitch up input of the stabilizer. A higher IAS to compensate the nose down effect. Much more thrust from the engine. A stability augmentation system to improve dynamic stability.

37 - In twin-engine aeroplanes with right turning propellers The left engine is the critical motor. The left engine produces a higher yaw moment if the right engine fails than vice versa. The right engine is the critical motor. The 'minimum control speed' is determined by the failure of the right engine.

38 - The speed of sound is affected by the: Temperature of the air. Humidity of the air. Pressure of the air. Density of the air.

39 - Excluding constants, the coefficient of induced drag (CDi) is the ratio of: CL and CD CL and b (wing span) CL2 and AR (aspect ratio) CL2and S (wing surface)

40 - Which kind of ''tab'' is commonly used in case of manual reversion of fully powered flight controls ? Servo tab Anti-balance tab Balance tab Spring tab

41 - If a symmetrical aerofoil is accelerated from subsonic to supersonic speed the aerodynamic centre will move Aft to the mid of the chord. Forward to the mid of the chord. Forward to the leading edge. Aft to the trailing edge.

42 - 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

43 - When the air is passing through a shock wave the static temperature will Stay constant. Decrease. Decrease and beyond a certain Mach number start increasing again Increase.

44 - Consider the steady flow through a stream tube where the velocity of the stream is V. An increase in temperature of the flow at a constant value of V will: Increase the mass flow Not affect the mass flow Decrease the mass flow Increase the mass flow when the tube is divergent in the direction of the flow

45 - For an aeroplane with one fixed value of VA the following applies. VA is: The speed at which unrestricted application of elevator control can be used, without exceeding the maximum manoeuvring limit load factor The maximum speed in smooth air Just another symbol for the rough air speed The speed at which the aeroplane stalls at the manoeuvring limit load factor at MTOW.

46 - 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

47 - An aeroplane has a servo tab controlled elevator. What will happen if the elevator jams during flight? Pitch control is lost. The servo-tab now works as a negative trim-tab. Pitch control sense is reversed. The pitch control forces double.

48 - 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.

49 - 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.

50 - Which point shown in the figure corresponds with CL for minimum horizontal flight speed?

Point a Point b Point d Point c

51 - 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.

52 - The lift force, acting on an aerofoil: Increases, proportional to the angle of attack until 40 degrees Is mainly caused by overpressure at the underside of the aerofoil Is mainly caused by suction on the upperside of the aerofoil Is maximum at an angle of attack of 2 degrees

53 - Assuming an initial condition in straight and level flight with CL = 1. What will be the new value of CL after the value of the speed has doubled? 0.25 2.00 1.00 0.50

54 - 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

55 - When comparing a rectangular wing and a swept back wing of the same wing area and wing loading, the swept back wing has the advantage of: Greater strength Increased longitudinal stability Higher critical Mach number Lower stalling speed

56 - 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.

57 - High speed buffet is induced by Boundary layer control. Expansion waves on the wing upper surface. Boundary layer separation due to shock wave formation. A shift of the centre of gravity.

58 - The unit of measurement of pressure is: Psi Kg/dm2 Lb/gal Kg/m3

59 - How are the speeds (shown in the figure) at point 1 and point 2 related to the relative wind / airflow V?

V1 = 0 and V2 > V V1 > V2 and V2 < V V1 = 0 and V2 = V V1 < V2 and V2 < V

60 - 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

61 - Induced drag at constant IAS is affected by: Aeroplane wing location Aeroplane weight Engine thrust Angle between wing chord and fuselage centre line

62 - When the air is passing through an expansion wave the static temperature will Increase. Stay constant. Decrease. Decrease and beyond a certain Mach number start increasing again.

63 - If an aeroplane flies in the ground effect The effective angle of attack is decreased The lift is increased and the drag is decreased Drag and lift are reduced The induced angle of attack is increased

64 - 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

65 - The angle of attack of a fixed pitch propeller blade increases when: Velocity and RPM increase Forward velocity increases and RPM decreasing RPM increases and forward velocity decreases Velocity and RPM decrease

66 - The function of the stick pusher is: To activate and push the stick forward prior to stick shaker To activate and push the stick forward at or beyond a certain value of angle of attack To pull the stick, to avoid a high speed stall To vibrate the controls

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

68 - Which type of flap is shown in the picture?

Double slotted flap Fowler flap Split flap Plain flap

69 - Increasing the number of propeller blades will: Increase the propeller efficiency Increase the noise level at maximum power Increase the maximum absorption of power Decrease the torque in the propeller shaft at maximum power

70 - Mcrit is the free stream Mach Number at which: Somewhere about the airframe Mach 1 is reached locally. The critical angle of attack is reached. Shockstall occurs. Mach buffet occurs.

71 - Which statement is correct?I. Stall speeds are determined with the CG at the aft limit.II. Minimum control speeds are determined with the CG at the forward limit. I is incorrect, II is incorrect. I is incorrect, II is correct. I is correct, II is incorrect. I is correct, II is correct.

72 - What increases the stalling angle of attack ? Use of: Spoilers Flaps Fuselage mounted speed-brakes Slats

73 - The true airspeed (TAS) is: Higher than the speed of the undisturbed airstream about the aeroplane Lower than the indicated airspeed (IAS) at ISA conditions and altitudes below sea level Lower than the speed of the undisturbed airstream about the aeroplane Equal to the IAS, multiplied by the air density at sea level

74 - 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.

75 - 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.

76 - The Mean Aerodynamic Chord (MAC) for a given wing of any planform is The chord of a large rectangular wing The average chord of the actual aeroplane The chord of a rectangular wing with same moment and lift The wing area divided by the wing span

77 - 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.

78 - A jet transport aeroplane exhibits pitch up when thrust is suddenly increased from an equilibrium condition, because the thrust line is below the: Drag line of action. CG. Centre of pressure. Neutral point.

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

Slat Krueger flap Slotted flap Fowler flap

80 - 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

81 - In order to maintain straight and level flight at a constant airspeed, whilst the flaps are being retracted, the angle of attack must be: Held constant Decreased Increased or decreased depending upon the type of flap Increased

82 - Rotation about the lateral axis is called: Yawing Slipping Pitching Rolling

83 - 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

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

85 - The following unit of measurement: kgm/s2 is expressed in the SI-system as: Newton Watt Joule Pascal

86 - The stall speed: Decreases with an increased weight Increases with an increased weight Increases with the length of the wingspan Does not depend on weight

87 - How is stall warning presented to the pilots of a large transport aeroplane? Stick shaker and / or aerodynamic buffet Aural warning only Stall warning light only Stick pusher

88 - An aeroplane has the following flap settings: 0°, 15°, 30° and 45°. Slats can also be selected. Which of the following selections will most adversely affect the CL / CD ratio? Flaps from 30° to 45° Flaps from 15° to 30° Flaps from 0° to 15° The slats

89 - Which line represents the total drag line of an aeroplane?

Line c Line d Line b Line a

90 - 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

91 - 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

92 - Which kind of boundary layer has the strongest change in velocity close to the surface? No difference Laminar boundary layer Transition boundary layer Turbulent boundary layer

93 - Compared with level flight prior to the stall, the lift ( 1) and drag ( 2) in the stall change as follows: (1) decreases (2) decreases (1) increases (2) increases (1) decreases (2) increases (1) increases (2) decreases

94 - If the elevator trim tab is deflected up, the cockpit trim indicator presents: Neutral Nose-down Nose-left Nose-up

95 - When trailing edge flaps are selected down whilst maintaining straight and level flight at constant IAS: The lift coefficient and the drag coefficient increase The stall speed increases The centre of pressure moves aft The total boundary layer becomes laminar

96 - The forces of lift and drag on an aerofoil are, respectively, normal and parallel to the: Chord line Relative wind / airflow Horizon Longitudinal axis

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

98 - Extension of FOWLER type trailing edge lift augmentation devices, will produce: A nose-up pitching moment No pitching moment A force which reduces drag A nose-down pitching moment

99 - The positive manoeuvring limit load factor for a light aeroplane in the utility category in the clean configuration is: 3.8 2.5 6.0 4.4

100 - Total pressure is: (rho = density) Static pressure plus dynamic pressure. Measured at a small hole in a surface, parallel to the local stream. 1/2 rho V2. Static pressure minus dynamic pressure.

101 - In order to perform a steady level turn at constant speed in an aeroplane, the pilot must: Increase thrust/power and keep angle of attack unchanged. Increase thrust/power and decrease angle of attack. Increase thrust/power and angle of attack. Increase angle of attack and keep thrust/power unchanged.

102 - 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.

103 - 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

104 - 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

105 - 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

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

107 - Which phenomenon is counteracted with differential aileron deflection? Aileron reversal. Sensitivity for spiral dive. Adverse yaw. Turn co-ordination.

108 - A jet aeroplane equipped with inboard and outboard ailerons is cruising at its normal cruise Mach number. In this case The inboard and outboard ailerons are active. Only the outboard aileron are active. Only the spoilers will be active, not the ailerons. Only the inboard ailerons are active.

109 - Low speed pitch up is caused by the: Spanwise flow on a swept back wing Mach trim system Wing tip vortex Spanwise flow on a swept forward wing

110 - What is the SI unit of measurement for power? Pa/m2 Kgm/s2 N/m Nm/s

111 - When are outboard ailerons (if present) de-activated? Flaps (and slats) retracted or speed above a certain value Landing gear extended Landing gear retracted Flaps (and/or slats) extended or speed below a certain value

112 - Which load factor determines VA? Manoeuvring limit load factor. Manoeuvring flap limit load factor. Gust load factor at 66 ft/sec gust. Manoeuvring ultimate load factor.

113 - A commercial jet aeroplane is performing a straight descent at a constant Mach number with constant mass. The operational speed limit that may be exceeded is: V VNE. MMO. VNE. MMO. VMO.

114 - 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

115 - What will happen in ground effect? The wing tip vortices increase in strength The wing downwash on the tail surfaces increases The thrust required will increase significantly The induced angle of attack and induced drag decrease

116 - In a steady level, co-ordinated turn, the load factor n and the stalling speed VS will be: N greater than 1, VS lower than in straight and level flight N smaller than 1, VS lower than in straight and level flight N smaller than 1, VS higher than in straight and level flight N greater than 1, VS higher than in straight and level flight

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

118 - 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

119 - The stall speed (IAS) will change according to the following factors: May increase with altitude, especially high altitude, will increase during icing conditions and will increase when the cg moves forward Will increase with increased load factor, more flaps and increased bank angle in a turn Will increase in a turn, higher temperature and will increase when the cg moves aft May increase when the cg moves forward, with higher altitude and due to the slipstream from a propeller on an engine located forward of the wing

120 - Where on the surface of a typical aerofoil will flow separation normally start at high angles of attack? Upper side trailing edge Lower side leading edge Lower side trailing edge Upper side leading edge

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