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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 - 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:
2 - 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):
3 - The aeroplane drag in straight and level flight is lowest when the:
4 - A jet transport aeroplane is in a straight climb at a constant IAS and constant weight. The operational limit that may be exceeded is:
5 - What data may be obtained from the Buffet Onset Boundary chart?
6 - The angle of attack of a two dimensional wing section is the angle between:
7 - The aspect ratio of the wing:
8 - Which combination of speeds is applicable for structural strength in gust (clean configuration)?
9 - Which of the following ( 1) aerofoils and ( 2) angles of attack will produce the lowest Mcrit values?
10 - 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:
11 - Ground effect has the following influence on the landing distance:
12 - Which statement about induced drag and tip vortices is correct?
13 - What wing shape or wing characteristic is the least sensitive to turbulence:
14 - What is the influence of decreasing aeroplane weight on Mcrit at constant IAS ?
15 - Which combination of design features is known to be responsible for deep stall?
16 - One disadvantage of wing sweep is the stalling characteristics. At the stall:
17 - A body is placed in a certain airstream. The airstream velocity increases by a factor 4. The aerodynamic drag will increase with a factor:
18 - 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:
19 - How does positive camber of an aerofoil affect static longitudinal stability?
20 - The wing of an aeroplane will never stall at low subsonic speeds as long as....
21 - The vane of a stall warning system with a flapper switch is activated by the change of the:
22 - How is adverse yaw compensated for during entry into and roll out from a turn ?
23 - Assuming no compressibility effects, induced drag at constant IAS is affected by:
24 - To increase the critical Mach number a conventional aerofoil should
25 - Dihedral of the wing is:
26 - Trailing edge flap extension will:
27 - 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)
28 - 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:
29 - Which statement about a jet transport aeroplane is correct during take-off with the cg at the forward limit and the trimmable horizontal stabiliser (THS) positioned at the maximum allowable aeroplane nose down position?
30 - After the transition point between the laminar and turbulent boundary layer
31 - Flap selection at constant IAS whilst maintaining straight and level flight will increase the:
32 - The aerodynamic centre of the wing is the point, where:
33 - During the take-off roll with a strong crosswind from the left, a four engine jet aeroplane with wing mounted engines experiences an engine failure above V1. Which engine causes the greatest control problem?
34 - When a strongly swept back wing stalls and the wake of the wing contacts the horizontal tail, the effect on the stall behaviour can be a(n):
35 - Rotation around the normal axis is called:
36 - Which line represents the total drag line of an aeroplane?
question pof9.webp
37 - Increase of the delta load factor due to a given vertical upgust at a given EAS occurs when:
38 - Air passes a normal shock wave. Which of the following statements is correct?
39 - In straight and level flight, as speed is increased:
40 - How can wing flutter be prevented?
41 - Which definition of propeller parameters is correct?
42 - The bank angle in a rate-one turn depends on:
43 - If the control column is pushed forward, a trim tab on the elevator:
44 - Differential aileron deflection:
45 - The polar curve of an aerofoil is a graphic relation between:
46 - On a symmetrical aerofoil, the pitching moment for which CL = 0 is:
47 - The forces of lift and drag on an aerofoil are, respectively, normal and parallel to the:
48 - 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.
49 - Consider an aerofoil with a certain camber and a positive angle of attack. At which location will the highest flow velocities occur?
50 - What increases the stalling angle of attack ? Use of:
51 - Which statement is correct about the laminar and turbulent boundary layer:
52 - In order to perform a steady level turn at constant speed in an aeroplane, the pilot must:
53 - Shock induced separation results in
54 - 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?
55 - High speed buffet is induced by
56 - Which of the following statements concerning control is correct?
57 - 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:
58 - VMO:
59 - 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?
60 - A slat will:
61 - The difference between IAS and TAS will:
62 - The critical Mach Number of an aeroplane is the free stream Mach Number, which produces the first evidence of:
63 - High Aspect Ratio, as compared with low Aspect Ratio, has the effect of:
64 - 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:
65 - When the air has passed through a normal shock wave the Mach number is
66 - An aeroplane exhibits static longitudinal stability, if, when the angle of attack changes:
67 - The correct drag formula is:
68 - Dangerous stall characteristics, in large transport aeroplanes that require stick pushers to be installed, include:
69 - A boundary layer fence on a swept wing will:
70 - Which statement is correct in respect of CL and angle of attack?
71 - Vortex generators:
72 - The stalling speed in IAS will change according to the following factors:
73 - The induced drag coefficient, CDi is proportional to:
74 - The angle of attack for a propeller blade is the angle between the blade chord line and the:
75 - 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:
76 - The maximum aft position of the centre of gravity is, amongst others, limited by the:
77 - The application of the area rule on aeroplane design will decrease the
78 - The angle of attack of a fixed pitch propeller blade increases when:
79 - Which statement about stick force per g is correct?
80 - The lift force, acting on an aerofoil:
81 - Which of the following statements about the difference between Krueger flaps and slats is correct?
82 - Which statement is correct about a normal shock wave ?
83 - The stall speed:
84 - The manoeuvrability of an aeroplane is best when the:
85 - If an aeroplane flies in the ground effect
86 - Which type of flap is shown in the picture?
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87 - The critical Mach number for an aerofoil equals the free stream airfoil Mach number at which:
88 - If you push forward the RPM lever of a constant speed propeller during a glide with idle power and constant speed, the propeller pitch will:
89 - During a climb at a constant IAS, the Mach Number:
90 - The lift formula is: (rho = density)
91 - An aeroplane performs a continuous descent with 160 KT IAS and 1000 fpm vertical speed. In this condition:
92 - 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:
93 - If the continuity equation is applicable, what will happen to the air density (rho) if the cross sectional area of a tube changes? (low speed, subsonic and incompressible flow)
94 - In what way do ( 1) induced drag and ( 2) parasite drag alter with increasing speed in straight and level flight?
95 - When 'spoilers' are used as speed brakes:
96 - Some aeroplanes have a 'waist' or 'coke bottle' contoured fuselage. This is done to
97 - Rotation about the lateral axis is called:
98 - In which phase of the take-off is the aerodynamic effect of ice located on the wing leading edge most critical?
99 - Where on the surface of a typical aerofoil will flow separation normally start at high angles of attack?
100 - What will increase the sensitivity to Dutch Roll?
101 - What is the purpose of an auto-slat system?
102 - VA is:
103 - A slotted flap will increase the CLmax by:
104 - When flaps are extended in a straight and level flight at constant IAS, the lift coefficient will eventually:
105 - Tick force per g is independent of altitude.II Stick force per g increases when the centre of gravity moves forward.
106 - An aeroplane performs a steady horizontal turn with a TAS of 200 KT. The turn radius is 2000m. The load factor (n) is approximately:
107 - 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?
108 - When trailing edge flaps are selected down whilst maintaining straight and level flight at constant IAS:
109 - Dihedral of the wing:
110 - The aft movement of the centre of pressure during acceleration through the transonic range will:
111 - Positive static stability of an aeroplane means that following a disturbance from the equilibrium condition:
112 - The SI units of air density (I) and force (II) are:
113 - The extreme right limitation for both V-n (gust and manoeuvre) diagrams is created by the speed:
114 - The stall speed increases, when: (all other factors of importance being constant)
115 - How are the speeds (shown in the figure) at point 1 and point 2 related to the relative wind / airflow V?
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116 - The flight Mach number is 0.8 and the TAS is 400 kts. The speed of sound is:
117 - By what percentage does VA (EAS) alter when the aeroplane's weight decreases by 19%?
118 - '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.
119 - Mass-balancing of control surfaces is used to:
120 - The high lift device shown in the figure below is a:
question pof5.webp
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