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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 effect on static stability of an aeroplane with a high wing as compared to a low wing is:
2 - When a pilot makes a turn in horizontal flight, the stall speed:
3 - Which of the following statements about the spin is correct?
4 - Examples of aerodynamic balancing of control surfaces are:
5 - Which statement follows from Bernoulli's equation for incompressible flow when total pressure remains constant?
6 - What should be usually done to perform a landing with the stabilizer jammed in the cruise flight position?
7 - The critical Mach number can be increased by
8 - 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?
9 - Which kind of boundary layer has the strongest change in velocity close to the surface?
10 - What will happen in ground effect?
11 - The (1) stick force stability and the (2) manoeuvre stability are positively affected by:
12 - Mcrit is the free stream Mach Number at which:
13 - Increase of the delta load factor due to a given vertical upgust at a given EAS occurs when:
14 - Just above the critical Mach number the first evidence of a shock wave will appear at the
15 - One important advantage the turbulent boundary layer has over the laminar layer is that:
16 - Which one of the following statements about the lift-to-drag ratio in straight and level flight is correct?
17 - Flaperons are controls which combine the function of:
18 - Rolling is the rotation of the aeroplane about the:
19 - A jet aeroplane is cruising at high altitude with a Mach-number, that provides a buffet margin of 0.3g incremental. In order to increase the buffet margin to 0.4g incremental the pilot must:
20 - If a symmetrical aerofoil is accelerated from subsonic to supersonic speed the aerodynamic centre will move
21 - When 'spoilers' are used as speed brakes:
22 - 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:
23 - One advantage of a movable-stabilizer system compared with an elevator trim system is that:
24 - 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?
25 - Increasing air density will have the following effect on the drag of a body in an airstream (angle of attack and TAS are constant):
26 - Which one of the following statements about Bernoulli's theorem is correct?
27 - What is the limit load factor of a large transport aeroplane?
28 - The use of a slot in the leading edge of the wing enables the aeroplane to fly at a slower speed because:
29 - The induced drag:
30 - Which of the following statements about the difference between Krueger flaps and slats is correct?
31 - By what percentage does VA (EAS) alter when the aeroplane's weight decreases by 19%?
32 - 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
33 - In which situation would the wing lift of an aeroplane in straight and level flight have the highest value?
34 - The loss of total pressure in a shock wave is due to the fact that
35 - The aft movement of the centre of pressure during acceleration through the transonic range will:
36 - An aeroplane exhibits static longitudinal stability, if, when the angle of attack changes:
37 - In order to perform a steady level turn at constant speed in an aeroplane, the pilot must:
38 - The angle between the aeroplane longitudinal axis and the chord line is the:
39 - The critical angle of attack:
40 - One method to compensate adverse yaw is:
41 - An aeroplane maintains straight and level flight while the IAS is doubled. The change in lift coefficient will be:
42 - The stall speed (IAS) will change according to the following factors:
43 - VA is:
44 - The induced angle of attack is the result of:
45 - Vortex generators mounted on the upper wing surface will
46 - 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:
47 - Critical Mach number is the free stream Mach number at which:
48 - 'Tuck under' is:
49 - In which phase of the take-off is the aerodynamic effect of ice located on the wing leading edge most critical?
50 - If you decrease the propeller pitch during a glide with idle-power at constant IAS the lift to drag ratio will:
51 - Consider an aerofoil with a certain camber and a positive angle of attack. At which location will the highest flow velocities occur?
52 - Bernoulli's law states: (note: rho is the mean sea level density under ISA conditions; pstat is static pressure; pdyn is dynamic pressure; ptot is total pressure)
53 - How is adverse yaw compensated for during entry into and roll out from a turn?
54 - When the air is passing through a shock wave the static temperature will
55 - Assuming ISA conditions, which statement with respect to the climb is correct?
56 - The manoeuvre stability of a large jet transport aeroplane is 280 N / g. What stick force is required, if the aeroplane is pulled to the limit manoeuvring load factor from a trimmed horizontal straight and steady flight? (cruise configuration)
57 - On a swept wing aeroplane at low airspeed, the 'pitch up' phenomenon:
58 - At an aeroplane's minimum drag speed, what is the ratio between induced drag Di and parasite drag Dp? Di / Dp =
59 - The high lift device shown in the figure below is a:
question pof5.webp
60 - The formula for the Mach Number is: (a= speed of sound)
61 - The angle of attack of a wing profile is defined as the angle between:
62 - What can happen to the aeroplane structure flying at a speed just exceeding VA?
63 - The manoeuvring speed VA expressed in indicated airspeed, of a transport aeroplane:
64 - Which of the following statements concerning control is correct?
65 - The extreme right limitation for both V-n (gust and manoeuvre) diagrams is created by the speed:
66 - 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.
67 - During the extension of the flaps at a constant angle of attack the aeroplane starts to (all other factors of importance being constant)
68 - Which of the following lists contain aeroplane design features that all increase static lateral stability?
69 - The Mean Aerodynamic Chord (MAC) for a given wing of any planform is
70 - What is the most effective flap system?
71 - An aeroplane performs a continuous descent with 160 KT IAS and 1000 fpm vertical speed. In this condition:
72 - The aeroplane drag in straight and level flight is lowest when the:
73 - In straight and level flight, as speed is reduced:
74 - Load factor is:
75 - An aeroplane performs a straight and level horizontal flight at the same angle of attack at two different altitudes. (all other factors of importance being constant, assume ISA conditions and no compressibility effects)
76 - What is the SI unit of measurement for power?
77 - The effect of a positive wing sweep on static directional stability is as follows:
78 - The torque effect during the take-off run in respect of a right hand propeller, when viewed from behind, will tend to:
79 - When air has passed through a shock wave the local speed of sound is:
80 - Which combination of design features is known to be responsible for deep stall?
81 - Which phenomenon is counteracted with differential aileron deflection?
82 - What factors determine the distance travelled over the ground of an aeroplane in a glide?
83 - The regime of flight from the critical Mach number up to approximately M = 1.3 is called the:
84 - The following factors increase stall speed:
85 - 'Tuck under' may happen at:
86 - Which statement is correct about a spring tab?
87 - The frontal area of a body, placed in a certain airstream is increased by a factor 3. The shape will not alter. The aerodynamic drag will increase with a factor:
88 - What data may be obtained from buffet onset boundary data?
89 - Static lateral stability will be increased by:
90 - The induced drag coefficient, CDi is proportional to:
91 - What is the advantage of a variable incidence tailplane over a fixed incidence tailplane with elevator and trim tab?
92 - 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.
93 - Which statement is correct at the speed for minimum drag (subsonic)?
94 - In what way do (1) induced drag and (2) parasite drag alter with increasing speed in straight and level flight?
95 - Compared with an oblique shock wave at the same Mach number a normal shock wave has a
96 - Compared with stalling airspeed (VS) in a given configuration, the airspeed at which stick shaker will be triggered is:
97 - Which of the following statements about stall speed is correct?
98 - The effect of the wing downwash on the static longitudinal stability of an aeroplane is:
99 - In what flight phase are the outboard ailerons (if present) not operated?
100 - An aeroplane should be equipped with a Mach trimmer, if:
101 - 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)
102 - Flap selection at constant IAS whilst maintaining straight and level flight will increase the:
103 - 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.
104 - The lift formula is:
105 - If an aeroplane flies in the ground effect
106 - The Mach number:
107 - In order to maintain straight and level flight at a constant airspeed, whilst the flaps are being retracted, the angle of attack must be:
108 - If in a two-dimensional incompressible and subsonic flow, the streamlines converge the static pressure in the flow will:
109 - The correct drag formula is:
110 - Gyroscopic precession of a propeller is induced by:
111 - 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?
112 - Does the pitch angle of a constant speed propeller alter in medium horizontal turbulence?
113 - When the air is passing through an expansion wave the static temperature will
114 - When Fowler type trailing edge flaps are extended at a constant angle of attack, the following changes will occur:
115 - The lift- and drag forces, acting on a wing cross section:
116 - Compared with level flight prior to the stall, the lift (1) and drag (2) in the stall change as follows:
117 - An engine failure can result in a windmilling (1) propeller and a feathered (2) propeller. Which statement about propeller drag is correct?
118 - One disadvantage of wing sweep is the stalling characteristics. At the stall:
119 - Mach buffet occurs:
120 - What increases the stalling angle of attack? Use of:
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