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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 - Compared with an oblique shock wave at the same Mach number a normal shock wave has a
2 - Which part of an aeroplane provides the greatest positive contribution to the static longitudinal stability ?
3 - The speed range between high- and low speed buffet:
4 - When air has passed through a shock wave the local speed of sound is:
5 - The gust load increases, when the altitude increases.
6 - An aeroplane transitions from steady straight and level flight into a horizontal co-ordinated turn with a load factor of 2, the speed remains constant and the:
7 - The manoeuvring speed VA expressed in indicated airspeed, of a transport aeroplane:
8 - Which of the following aeroplane parts affect induced drag most?
9 - Vortex generators on the upper side of the wing surface will:
10 - One method to compensate adverse yaw is:
11 - 'Flutter' may be caused by:
12 - Which load factor determines VA?
13 - The units of wing loading (I) W / S and (II) dynamic pressure q are:
14 - In twin-engine aeroplanes with right turning propellers
15 - Which combination of speeds is applicable for structural strength in gust (clean configuration)?
16 - A plain flap will increase CLmax by
17 - What data may be obtained from the Buffet Onset Boundary chart?
18 - The maximum acceptable cruising altitude is limited by a minimum acceptable loadfactor because exceeding that altitude:
19 - What is the effect on induced drag of mass and speed changes? (all other factors of importance remaining constant)
20 - An aeroplane maintains straight and level flight while the IAS is doubled. The change in lift coefficient will be:
21 - The flight Mach number is 0.8 and the TAS is 400 kts. The speed of sound is:
22 - Gyroscopic precession of a propeller is induced by:
23 - Extension of FOWLER type trailing edge lift augmentation devices, will produce:
24 - 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:
25 - Which of the following lists contain aeroplane design features that all increase static lateral stability?
26 - An engine failure can result in a windmilling ( 1) propeller and a feathered ( 2) propeller. Which statement about propeller drag is correct?
27 - At higher altitudes, the stall speed (IAS):
28 - Tick force per g is independent of altitude.II Stick force per g increases when the centre of gravity moves forward.
29 - Which point shown in the figure corresponds with CL for minimum horizontal flight speed?
question pof7.webp
30 - The lift formula is: (rho = density)
31 - 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:
32 - High speed buffet is induced by
33 - How will the density and static temperature change in a supersonic flow from a position in front of a shock wave to behind it ?
34 - The angle of attack of a fixed pitch propeller blade increases when:
35 - What is the most effective flap system?
36 - The pitching moment versus angle of attack line in the diagram, which corresponds to a CG located at the neutral point of of a given aeroplane at low and moderate angles of attack is:
question pof13.webp
37 - 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:
38 - How is stall warning presented to the pilots of a large transport aeroplane?
39 - 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:
40 - If the trailing edge flaps are lowered (fully extended), in order to maintain constant IAS and level flight:
41 - The value of the parasite drag in straight and level flight at constant weight varies linearly with the:
42 - One important advantage the turbulent boundary layer has over the laminar layer is that:
43 - Vortex generators on the upper side of the wing:
44 - Which one of the following statements about the lift-to-drag ratio in straight and level flight is correct?
45 - Dihedral of the wing:
46 - When the Mach number is slowly increased in straight and level flight the first shockwaves will occur:
47 - The high lift device shown in the figure below is a:
question pof5.webp
48 - Which of the following statements about the difference between Krueger flaps and slats is correct?
49 - Mcrit is the free stream Mach Number at which:
50 - At an aeroplane's minimum drag speed, what is the ratio between induced drag Di and parasite drag Dp? Di / Dp =
51 - If the control column is pushed forward, a trim tab on the elevator:
52 - In which situation would the wing lift of an aeroplane in straight and level flight have the highest value?
53 - The positive manoeuvring limit load factor for a large jet transport aeroplane with flaps extended is:
54 - The aerodynamic drag of a body, placed in a certain airstream depends amongst others on:
55 - The Mach-trim function is installed on most commercial jets in order to minimize the adverse effects of:
56 - The aft movement of the centre of pressure during acceleration through the transonic range will:
57 - How does stalling speed (IAS) vary with altitude?
58 - Which statement about stick force per g is correct?
59 - The loss of total pressure in a shock wave is due to the fact that
60 - The use of a slot in the leading edge of the wing enables the aeroplane to fly at a slower speed because:
61 - The following factors increase stall speed:
62 - Which of the following statements is true?
63 - Load factor is:
64 - In the transonic range the aeroplane characteristics are strongly determined by:
65 - In which phase of the take-off is the aerodynamic effect of ice located on the wing leading edge most critical?
66 - What is the purpose of an auto-slat system?
67 - An aeroplane has static directional stability
68 - Which of the following statements about the spin is correct?
69 - What can happen to the aeroplane structure flying at a speed just exceeding VA ?
70 - The stall speed in a 60° banked turn increases by the following factor:
71 - Bernoulli's law states:(note: rho is the mean sea level density under ISA conditions
72 - Drag is in the direction of - and lift is perpendicular to the:
73 - Induced drag may be reduced by:
74 - Which of the following will reduce induced drag?
75 - When 'spoilers' are used as speed brakes:
76 - 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)
77 - The pitch up effect of an aeroplane with swept wing in a stall is due to the
78 - When trailing edge flaps are selected down whilst maintaining straight and level flight at constant IAS:
79 - By what percentage does VA (EAS) alter when the aeroplane's weight decreases by 19%?
80 - Which has the effect of increasing load factor ? (all other relevant factors being constant)
81 - An aeroplane is descending at a constant Mach number from FL 350. What is the effect on true airspeed ?
82 - The aerodynamic contribution to the static longitudinal stability of the nacelles of aft fuselage mounted engines is:
83 - In order to perform a steady level turn at constant speed in an aeroplane, the pilot must:
84 - The aspect ratio of the wing:
85 - The lift of an aeroplane of weight W in a constant linear climb with a climb angle (gamma) is approximately:
86 - The SI units of air density (I) and force (II) are:
87 - When Fowler type trailing edge flaps are extended at a constant angle of attack, the following changes will occur:
88 - Deploying a Fowler flap, the flap will:
89 - Which statement is correct at the speed for minimum drag (subsonic) ?
90 - For an aeroplane with one fixed value of VA the following applies. VA is:
91 - The angle of attack of a wing profile is defined as the angle between:
92 - If the total sum of moments about one of its axes is not zero, an aeroplane would:
93 - Static lateral stability should not be too small, because:
94 - A body is placed in a certain airstream. The airstream velocity increases by a factor 4. The aerodynamic drag will increase with a factor:
95 - 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.
96 - 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:
97 - Constant-speed propellers provide a better performance than fixed-pitch propellers because they:
98 - VMO:
99 - A laminar boundary layer is a layer, in which:
100 - If you decrease the propeller pitch during a glide with idle-power at constant IAS the lift to drag ratio will:
101 - 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?
102 - Critical Mach number is the free stream Mach number at which:
103 - High Aspect Ratio, as compared with low Aspect Ratio, has the effect of:
104 - The polar curve of an aerofoil is a graphic relation between:
105 - Given an initial condition in straight and level flight with a speed of 1.4 VS. The maximum bank angle attainable without stalling in a steady co-ordinated turn, whilst maintaining speed and altitude, is approximately:
106 - On an asymmetrical, single curve aerofoil, in subsonic airflow, at low angle of attack, when the angle of attack is increased, the centre of pressure will (assume a conventional transport aeroplane):
107 - The ( 1) stick force stability and the ( 2) manoeuvre stability are positively affected by:
108 - If the elevator trim tab is deflected up, the cockpit trim indicator presents:
109 - The location of the centre of pressure of a positive cambered wing at increasing angle of attack will:
110 - The point, where the single resultant aerodynamic force acts on an aerofoil, is called:
111 - The continuity equation states: If the area of a tube is increasing, the speed of the subsonic and incompressible flow inside is
112 - If the nose of an aeroplane yaws left, this causes:
113 - The critical Mach number for an aerofoil equals the free stream airfoil Mach number at which:
114 - The bank angle in a rate-one turn depends on:
115 - The true airspeed (TAS) is:
116 - '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.
117 - Compared with stalling airspeed (VS) in a given configuration, the airspeed at which stick shaker will be triggered is:
118 - How does positive camber of an aerofoil affect static longitudinal stability?
119 - The angle between the aeroplane longitudinal axis and the chord line is the:
120 - Examples of aerodynamic balancing of control surfaces are:
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