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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 wing of an aeroplane will never stall at low subsonic speeds as long as....
2 - The induced angle of attack is the result of:
3 - The relative thickness of an aerofoil is expressed as:
4 - Mcrit is the free stream Mach Number at which:
5 - The terms 'q' and 'S' in the lift formula are:
6 - The aeroplane drag in straight and level flight is lowest when the:
7 - Flap selection at constant IAS whilst maintaining straight and level flight will increase the:
8 - The manoeuvrability of an aeroplane is best when the:
9 - An engine failure can result in a windmilling (1) propeller and a feathered (2) propeller. Which statement about propeller drag is correct?
10 - Induced drag is created by the:
11 - Dangerous stall characteristics, in large transport aeroplanes that require stick pushers to be installed, include:
12 - 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?
13 - Positive static longitudinal stability means that a:
14 - The lift force, acting on an aerofoil:
15 - The value of the parasite drag in straight and level flight at constant weight varies linearly with the:
16 - 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:
17 - Which type of flap is shown in the picture?
question pof1.webp
18 - When the air is passing through an expansion wave the Mach number will
19 - Considering a positive cambered aerofoil, the pitching moment when CL = 0 is:
20 - Regarding flight in severe turbulence, which of the following statements is true?
21 - Which aeroplane behaviour will be corrected by a yaw damper?
22 - 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.
23 - Spoiler deflection causes:
24 - 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?
25 - One disadvantage of wing sweep is the stalling characteristics. At the stall:
26 - Rolling is the rotation of the aeroplane about the:
27 - The positive manoeuvring limit load factor for a light aeroplane in the utility category in the clean configuration is:
28 - Compared with an oblique shock wave at the same Mach number a normal shock wave has a
29 - When air has passed through a shock wave the local speed of sound is:
30 - The critical Mach number can be increased by
31 - The effect on static stability of an aeroplane with a high wing as compared to a low wing is:
32 - 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:
33 - The pitching moment versus angle of attack line in the diagram, which corresponds to a CG located at the neutral point of a given aeroplane at low and moderate angles of attack is:
question pof13.webp
34 - The regime of flight from the critical Mach number up to approximately M = 1.3 is called the:
35 - Which of the following statements about stall speed is correct?
36 - Given the following aeroplane configurations: 1. Clean wing 2. Slats only extended 3. Flaps only extended Place these configurations in order of stall angle of attack:
37 - If the trailing edge flaps are lowered (fully extended), in order to maintain constant IAS and level flight:
38 - The function of the slot between an extended slat and the leading edge of the wing is to:
39 - Comparing the lift coefficient and drag coefficient at normal angle of attack:
40 - What is the most effective flap system?
41 - Which combination of speeds is applicable for structural strength in gust (clean configuration)?
42 - The lift formula is: (rho = density)
43 - The speed range between high- and low speed buffet:
44 - Load factor is:
45 - The function of the stick pusher is:
46 - What will increase the sensitivity to Dutch Roll?
47 - Bernoulli's equation can be written as: (pt= total pressure, ps = static pressure and q=dynamic pressure)
48 - 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?
49 - 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?
50 - Which one of the following statements about the lift-to-drag ratio in straight and level flight is correct?
51 - The speed of sound is affected by the:
52 - The Mach-trim function is installed on most commercial jets in order to minimize the adverse effects of:
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?
54 - The 'short period mode' is an:
55 - If an aeroplane is accelerated from subsonic to supersonic speeds, the centre of pressure will move:
56 - If a symmetrical aerofoil is accelerated from subsonic to supersonic speed the aerodynamic centre will move
57 - During landing of a low-winged jet aeroplane, the greatest elevator up deflection is normally required when the flaps are:
58 - When the air is passing through an expansion wave the static temperature will
59 - 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:
60 - The loss of total pressure in a shock wave is due to the fact that
61 - The effects of very heavy rain (tropical rain) on the aerodynamic characteristics of an aeroplane are:
62 - In case the Mach trimmer fails:
63 - The Mean Aerodynamic Chord (MAC) for a given wing of any planform is
64 - The angle of attack of a fixed pitch propeller blade increases when:
65 - A slat will:
66 - By what percentage does the lift increase in a level turn at 45° angle of bank, compared to straight and level flight?
67 - The stall speed in a 60° banked turn increases by the following factor:
68 - In twin-engine aeroplanes with right turning propellers
69 - The vane of a stall warning system with a flapper switch is activated by the change of the:
70 - Does the pitch angle of a constant speed propeller alter in medium horizontal turbulence?
71 - Deploying a Fowler flap, the flap will:
72 - Which of the following flight phenomena can occur at Mach numbers below the critical Mach number?
73 - Drag is in the direction of - and lift is perpendicular to the:
74 - The pitch up effect of an aeroplane with swept wing in a stall is due to the
75 - The angle of attack of a wing profile is defined as the angle between:
76 - If the nose of an aeroplane yaws left, this causes:
77 - In the transonic range lift will decrease at the shock stall due to the
78 - Which statement about stick force per g is correct?
79 - Which kind of ''tab'' is commonly used in case of manual reversion of fully powered flight controls?
80 - If the control column is pushed forward, a trim tab on the elevator:
81 - Increasing the number of propeller blades will:
82 - An aeroplane maintains straight and level flight while the IAS is doubled. The change in lift coefficient will be:
83 - 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.
84 - 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:
85 - Where on the surface of a typical aerofoil will flow separation normally start at high angles of attack?
86 - In what way do (1) induced drag and (2) parasite drag alter with increasing speed in straight and level flight?
87 - In order to maintain straight and level flight at a constant airspeed, whilst the flaps are being retracted, the angle of attack must be:
88 - The stall speed (IAS) will change according to the following factors:
89 - Compared with level flight prior to the stall, the lift (1) and drag (2) in the stall change as follows:
90 - How are the speeds (shown in the figure) at point 1 and point 2 related to the relative wind / airflow V?
question pof6.webp
91 - Induced drag may be reduced by:
92 - During initiation of a turn with speedbrakes extended, the roll spoiler function induces a spoiler deflection:
93 - VMO:
94 - The maximum aft position of the centre of gravity is, amongst others, limited by the:
95 - The effect of the wing downwash on the static longitudinal stability of an aeroplane is:
96 - What is the position of the elevator in relation to the trimmable horizontal stabiliser of a power assisted aeroplane that is in trim?
97 - An aeroplane exhibits static longitudinal stability, if, when the angle of attack changes:
98 - The torque effect during the take-off run in respect of a right hand propeller, when viewed from behind, will tend to:
99 - At an aeroplane's minimum drag speed, what is the ratio between induced drag Di and parasite drag Dp? Di / Dp =
100 - When are outboard ailerons (if present) de-activated?
101 - For an aeroplane with one fixed value of VA the following applies. VA is:
102 - The location of the centre of pressure of a positive cambered wing at increasing angle of attack will:
103 - 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?
104 - Increase of wing loading will:
105 - Which of the following (1) aerofoils and (2) angles of attack will produce the lowest Mcrit values?
106 - An aeroplane has the following flap positions: 0°, 15°, 30°, 45°. Slats can also be selected. Generally speaking, which selection provides the highest positive contribution to the CLMAX?
107 - The difference between IAS and TAS will:
108 - A jet transport aeroplane exhibits pitch up when thrust is suddenly increased from an equilibrium condition, because the thrust line is below the:
109 - The use of a slot in the leading edge of the wing enables the aeroplane to fly at a slower speed because:
110 - The flight Mach number is 0.8 and the TAS is 400 kts. The speed of sound is:
111 - If the total sum of moments about one of its axes is not zero, an aeroplane would:
112 - What is the SI unit of measurement for power?
113 - Which statement is correct about a spring tab?
114 - Increasing dynamic pressure will have the following effect on the drag of an aeroplane (all other factors of importance remaining constant):
115 - Following a disturbance, an aeroplane oscillates about the lateral axis at a constant amplitude. The aeroplane is:
116 - Which combination of design features is known to be responsible for deep stall?
117 - Which load factor determines VA?
118 - Extension of FOWLER type trailing edge lift augmentation devices, will produce:
119 - Just above the critical Mach number the first evidence of a shock wave will appear at the
120 - The trailing edge flaps when extended:
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