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Exam simulation Principles of Flight ATPL - Airline Transport Pilot license

Exam simulation ATPL Principles of Flight 120 questions on 120 minutes

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1 - The critical Mach Number of an aeroplane can be increased by:
2 - 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:
3 - 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 - The boundary layer of a wing is:
5 - Positive static longitudinal stability means that a:
6 - Which one of the following statements about Bernoulli's theorem is correct?
7 - Increase of the delta load factor due to a given vertical upgust at a given EAS occurs when:
8 - Which of the following statements about dihedral is correct?
9 - The stall speed:
10 - The stall speed in a 60° banked turn increases by the following factor:
11 - By what percentage does the lift increase in a level turn at 45° angle of bank, compared to straight and level flight?
12 - Differential aileron deflection:
13 - Rotation about the lateral axis is called:
14 - Extension of FOWLER type trailing edge lift augmentation devices, will produce:
15 - The critical Mach number can be increased by
16 - The (1) stick force stability and the (2) manoeuvre stability are positively affected by:
17 - Consider an aerofoil with a certain camber and a positive angle of attack. At which location will the highest flow velocities occur?
18 - Static lateral stability should not be too small, because:
19 - The unit of density is:
20 - Which load factor determines VA?
21 - 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?
22 - At higher altitudes, the stall speed (IAS):
23 - I. Stick force per g is independent of altitude. II. Stick force per g increases when the centre of gravity moves forward.
24 - A laminar boundary layer is a layer, in which:
25 - One disadvantage of wing sweep is the stalling characteristics. At the stall:
26 - The aerodynamic centre of the wing is the point, where:
27 - The angle of attack of a wing profile is defined as the angle between:
28 - When trailing edge flaps are selected down whilst maintaining straight and level flight at constant IAS:
29 - When the Mach number is slowly increased in straight and level flight the first shockwaves will occur:
30 - Which statement is correct about the laminar and turbulent boundary layer:
31 - Trailing edge flap extension will:
32 - The critical Mach number for an aerofoil equals the free stream airfoil Mach number at which:
33 - The bow wave will first appear at:
34 - Which statement is correct about a normal shock wave?
35 - When the air has passed through a normal shock wave the Mach number is
36 - Compared with stalling airspeed (VS) in a given configuration, the airspeed at which stick shaker will be triggered is:
37 - If a symmetrical aerofoil is accelerated from subsonic to supersonic speed the aerodynamic centre will move
38 - 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:
39 - If the trailing edge flaps are lowered (fully extended), in order to maintain constant IAS and level flight:
40 - Consider an aeroplane with: 1 a trim tab. 2 fully powered hydraulic controls and an adjustable horizontal stabiliser. For both cases and starting from a trimmed condition, how will the neutral position of the control column change, after trimming for a speed increase?
41 - If the nose of an aeroplane yaws left, this causes:
42 - Induced drag may be reduced by:
43 - An aeroplane has a stall speed of 100 KT at a load factor n = 1. In a turn with a load factor of n = 2, the stall speed is:
44 - The aft movement of the centre of pressure during acceleration through the transonic range will:
45 - The trailing edge flaps when extended:
46 - The lift coefficient (CL) of an aeroplane in steady horizontal flight is 0.42. An increase in angle of attack of 1 degree increases CL by 0.1. A vertical up gust instantly changes the angle of attack by 3 degrees. The load factor will be:
47 - The forces of lift and drag on an aerofoil are, respectively, normal and parallel to the:
48 - Which line represents the total drag line of an aeroplane?
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49 - VA is:
50 - Given two identical aeroplanes with wing mounted engines, one fitted with jet engines and the other with counter rotating propellers, what happens following an engine failure?
51 - Which aeroplane behaviour will be corrected by a yaw damper?
52 - 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:
53 - Which kind of ''tab'' is commonly used in case of manual reversion of fully powered flight controls?
54 - A slotted flap will increase the CLmax by:
55 - In a twin engine jet aeroplane (engines mounted below the low wings) the thrust is suddenly increased. Which elevator deflection will be required to maintain the pitching moment zero?
56 - During the extension of the flaps at a constant angle of attack the aeroplane starts to (all other factors of importance being constant)
57 - The speed of sound is affected by the:
58 - If an aeroplane exhibits insufficient stick force per g, this problem can be resolved by installing:
59 - What should be usually done to perform a landing with the stabilizer jammed in the cruise flight position?
60 - The regime of flight from the critical Mach number up to approximately M = 1.3 is called the:
61 - Compared with level flight prior to the stall, the lift (1) and drag (2) in the stall change as follows:
62 - During an erect spin recovery:
63 - Increasing air density will have the following effect on the drag of a body in an airstream (angle of attack and TAS are constant):
64 - Which one of the following systems suppresses the tendency to 'Dutch roll'?
65 - Which statement is correct? The lift to drag ratio determines the
66 - In straight and level flight, as speed is reduced:
67 - During a climb at a constant IAS, the Mach Number:
68 - The lift formula is:
69 - With increasing altitude and constant IAS the static lateral stability (1) and the dynamic lateral/directional stability (2) of an aeroplane with swept-back wing will:
70 - The aerodynamic drag of a body, placed in a certain airstream depends amongst others on:
71 - When a pilot makes a turn in horizontal flight, the stall speed:
72 - What is the position of the elevator in relation to the trimmable horizontal stabiliser of a power assisted aeroplane that is in trim?
73 - The use of a slot in the leading edge of the wing enables the aeroplane to fly at a slower speed because:
74 - Which combination of design features is known to be responsible for deep stall?
75 - 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:
76 - The airload on the horizontal tailplane (tailload) of an aeroplane in straight and level flight:
77 - An aeroplane maintains straight and level flight while the IAS is doubled. The change in lift coefficient will be:
78 - Which statement about a primary control surface controlled by a servo tab, is correct?
79 - The lift force, acting on an aerofoil:
80 - In general transport aeroplanes with power assisted flight controls are fitted with an adjustable stabilizer instead of trim tabs on the elevator. This is because:
81 - In the transonic range the aeroplane characteristics are strongly determined by:
82 - Which part of an aeroplane provides the greatest positive contribution to the static longitudinal stability?
83 - Excluding constants, the coefficient of induced drag (CDi) is the ratio of:
84 - 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?
85 - What is the influence of decreasing aeroplane weight on Mcrit at constant IAS?
86 - Which of the following statements about the stall of a straight wing aeroplane is correct?
87 - After the transition point between the laminar and turbulent boundary layer
88 - Induced drag at constant IAS is affected by:
89 - 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:
90 - The point, where the single resultant aerodynamic force acts on an aerofoil, is called:
91 - 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?
92 - Which of the following wing planforms gives the highest local lift coefficient at the wing root?
93 - Considering a positive cambered aerofoil, the pitching moment when CL = 0 is:
94 - 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.
95 - During landing of a low-winged jet aeroplane, the greatest elevator up deflection is normally required when the flaps are:
96 - Upon extension of a spoiler on a wing:
97 - On a swept wing aeroplane at low airspeed, the 'pitch up' phenomenon:
98 - When the air is passing through a shock wave the static temperature will
99 - Interference drag is the result of:
100 - Just above the critical Mach number the first evidence of a shock wave will appear at the
101 - Static pressure acts:
102 - The lift coefficient (CL) of an aeroplane in steady horizontal flight is 0.4. An increase in angle of attack of 1 degree will increase CL by 0.09. A vertical up gust instantly changes the angle of attack by 5 degrees. The load factor will be:
103 - Which of the following will reduce induced drag?
104 - Which statement is correct? I. Propeller gyroscopic effect occurs during aeroplane yaw changes. II. Propeller gyroscopic effect is most noticeable during low speed flight at high propeller RPM.
105 - For a fixed-pitch propeller in flight at a given TAS, the blade angle of attack will:
106 - '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.
107 - 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.
108 - The continuity equation states: If the area of a tube is increasing, the speed of the subsonic and incompressible flow inside is
109 - What can happen to the aeroplane structure flying at a speed just exceeding VA?
110 - The pitch up effect of an aeroplane with swept wing in a stall is due to the
111 - 'Tuck under' may happen at:
112 - During the retraction of the flaps at a constant angle of attack the aeroplane starts to (all other factors of importance being constant):
113 - The high lift device shown in the figure below is a:
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114 - Deflection of leading edge flaps will:
115 - The effect on static stability of an aeroplane with a high wing as compared to a low wing is:
116 - Which of the following wing planforms produces the lowest induced drag? (all other relevant factors constant)
117 - What is the effect on induced drag of mass and speed changes? (all other factors of importance remaining constant)
118 - An aeroplane performs a continuous descent with 160 KT IAS and 1000 fpm vertical speed. In this condition:
119 - On a symmetrical aerofoil, the pitching moment for which CL = 0 is:
120 - Which of the following statements about stall speed is correct?
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