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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 correct drag formula is:
2 - Induced drag is created by the:
3 - An aeroplane has static directional stability
4 - Which statement about stick force per g is correct?
5 - The diagram shows the parameter X versus TAS. If a horizontal flight is considered the axis X shows
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6 - High speed buffet is induced by
7 - What factors determine the distance travelled over the ground of an aeroplane in a glide ?
8 - The effect on static stability of an aeroplane with a high wing as compared to a low wing is:
9 - 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:
10 - During landing of a low-winged jet aeroplane, the greatest elevator up deflection is normally required when the flaps are:
11 - The vane of a stall warning system with a flapper switch is activated by the change of the:
12 - 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?
13 - 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:
14 - 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:
15 - When the air is passing through a shock wave the static temperature will
16 - What wing shape or wing characteristic is the least sensitive to turbulence:
17 - The torque effect during the take off run in respect of a right hand propeller, when viewed from behind, will tend to:
18 - When air has passed through a shock wave the local speed of sound is:
19 - What will happen in ground effect?
20 - 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:
21 - In the transonic range the aeroplane characteristics are strongly determined by:
22 - When the air is passing through an expansion wave the static temperature will
23 - Tuck under will happen
24 - A line connecting the leading edge and trailing edge midway between the upper and lower surface of an aerofoil.This definition is applicable for:
25 - Positive static longitudinal stability means that a:
26 - A body is placed in a certain airstream. The airstream velocity increases by a factor 4. The aerodynamic drag will increase with a factor:
27 - The aeroplane drag in straight and level flight is lowest when the:
28 - The induced drag:
29 - When the Mach number is slowly increased in straight and level flight the first shockwaves will occur:
30 - When the air has passed through a normal shock wave the Mach number is
31 - The boundary layer of a wing is:
32 - Deflection of leading edge flaps will:
33 - 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:
34 - Which of the following statements about a constant speed propeller is correct?
35 - Winglets
36 - 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?
37 - 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?
38 - 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?
39 - 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.
40 - 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):
41 - 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 ?
42 - Extension of FOWLER type trailing edge lift augmentation devices, will produce:
43 - Spoiler deflection causes:
44 - By what percentage does VA (EAS) alter when the aeroplane's weight decreases by 19%?
45 - Increasing air density will have the following effect on the drag of a body in an airstream (angle of attack and TAS are constant):
46 - The critical Mach number can be increased by
47 - The function of the stick pusher is:
48 - Vortex generators on the upper side of the wing:
49 - After take-off the slats (when installed) are always retracted later than the flaps. Why?
50 - Which aeroplane design has the highest probability of a super stall?
51 - When a pilot makes a turn in horizontal flight, the stall speed:
52 - The unit of density is:
53 - Air passes a normal shock wave. Which of the following statements is correct?
54 - Which of the following ( 1) aerofoils and ( 2) angles of attack will produce the lowest Mcrit values?
55 - 'Tuck under' may happen at:
56 - Which statement is correct?The lift to drag ratio determines the
57 - Vortex generators mounted on the upper wing surface will
58 - Rotation around the normal axis is called:
59 - Which combination of speeds is applicable for structural strength in gust (clean configuration)?
60 - In order to perform a steady level turn at constant speed in an aeroplane, the pilot must:
61 - When a jet transport aeroplane takes off with the CG at the forward limit and the trimmable horizontal stabiliser (THS) is positioned at the maximum allowable nose up position for take- off:
62 - An engine failure can result in a windmilling ( 1) propeller and a feathered ( 2) propeller. Which statement about propeller drag is correct?
63 - When Fowler type trailing edge flaps are extended at a constant angle of attack, the following changes will occur:
64 - 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:
65 - Which kind of boundary layer has the strongest change in velocity close to the surface?
66 - Which of the following situations leads to a decreasing stall speed (IAS)?
67 - In order to maintain straight and level flight at a constant airspeed, whilst the flaps are being retracted, the angle of attack must be:
68 - Which formula or equation describes the relationship between force (F), acceleration (a) and mass (m)?
69 - Tick force per g is independent of altitude.II Stick force per g increases when the centre of gravity moves forward.
70 - Which of the following statements about the difference between Krueger flaps and slats is correct?
71 - During the retraction of the flaps at a constant angle of attack the aeroplane starts to (all other factors of importance being constant):
72 - Critical Mach number is the free stream Mach number at which:
73 - What is the effect of high aspect ratio of an aeroplane's wing on induced drag?
74 - In the transonic range lift will decrease at the shock stall due to the
75 - 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?
76 - A boundary layer fence on a swept wing will:
77 - The flight Mach number is 0.8 and the TAS is 400 kts. The speed of sound is:
78 - If you decrease the propeller pitch during a glide with idle-power at constant IAS the lift to drag ratio will:
79 - Assuming ISA conditions, which statement with respect to the climb is correct ?
80 - 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)
81 - Which of the following wing planforms produces the lowest induced drag? (all other relevant factors constant)
82 - Which of the following statements concerning control is correct?
83 - Upon extension of a spoiler on a wing:
84 - The use of a slot in the leading edge of the wing enables the aeroplane to fly at a slower speed because:
85 - Vortex generators:
86 - Constant-speed propellers provide a better performance than fixed-pitch propellers because they:
87 - Considering a positive cambered aerofoil, the pitching moment when CL = 0 is:
88 - The stalling speed in IAS will change according to the following factors:
89 - Compared with stalling airspeed (VS) in a given configuration, the airspeed at which stick shaker will be triggered is:
90 - The CL - alpha curve of a positive cambered aerofoil intersects with the vertical axis of the CL- alpha graph:
91 - A jet transport aeroplane is in a straight climb at a constant IAS and constant weight. The operational limit that may be exceeded is:
92 - A slat will:
93 - 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:
94 - After the transition point between the laminar and turbulent boundary layer
95 - Which part of an aeroplane provides the greatest positive contribution to the static longitudinal stability ?
96 - The aerodynamic contribution to the static longitudinal stability of the nacelles of aft fuselage mounted engines is:
97 - Deploying a Fowler flap, the flap will:
98 - Which has the effect of increasing load factor ? (all other relevant factors being constant)
99 - In case the Mach trimmer fails:
100 - Where on the surface of a typical aerofoil will flow separation normally start at high angles of attack?
101 - The airload on the horizontal tailplane (tailload) of an aeroplane in straight and level flight:
102 - 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?
103 - The most important problem of ice accretion on a transport aeroplane during flight is:
104 - The application of the area rule on aeroplane design will decrease the
105 - Static pressure acts:
106 - What is the most effective flap system?
107 - Compared with an oblique shock wave at the same Mach number a normal shock wave has a
108 - When an aircraft is rolled to the left, adverse yaw will be reduced by:
109 - An aeroplane has a stall speed of 78 KCAS at its gross weight of 6850 lbs. What is the stall speed when the weight is 5000 lbs?
110 - The positive manoeuvring limit load factor for a light aeroplane in the utility category in the clean configuration is:
111 - High Aspect Ratio, as compared with low Aspect Ratio, has the effect of:
112 - Positive static stability of an aeroplane means that following a disturbance from the equilibrium condition:
113 - If you pull back the RPM lever of a constant speed propeller during a glide with idle power and constant speed, the propeller pitch will:
114 - Interference drag is the result of:
115 - Low speed pitch up is caused by the:
116 - The lift formula is:
117 - An aeroplane exhibits static longitudinal stability, if, when the angle of attack changes:
118 - Which statement is correct in respect of CL and angle of attack?
119 - To increase the critical Mach number a conventional aerofoil should
120 - Increase of the delta load factor due to a given vertical upgust at a given EAS occurs when:
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