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CPL Test Series
Question Bank
Questions for INDIGO AERODYNAMIC 5259-5689
Answer the following questions
Test Mode
Training Mode
1.
What is the limit load factor of a large transport aeroplane in the manoeuvring diagram?
6
2.5
1.5
3.75
2.
When the air has passed through a normal shock wave the Mach number is
higher than before
less than 1.
lower than before but still greater than 1.
equal to 1.
3.
When air has passed an expansion wave, the static pressure is
decreased or increased, depending on Mach Number.
unchanged.
decreased.
increased.
4.
The value of the manoeuvre stability of an aeroplane is 150 N/g. The load factor in straight and level flight is 1. The increase of stick force necessary to achieve the load factor of 2.5 is
375 N.
450 N.
150 N.
225 N.
5.
A jet aeroplane is rolled into a turn, while maintaining airspeed and holding altitude. In such a case, the pilot has to
increase angle of attack and keep thrust unchanged.
increase thrust and keep angle of attack unchanged.
increase thrust and decrease angle of attack
increase thrust and angle of attack
6.
A propeller is turning to the right, seen from behind. The asymmetric thrust effect is mainly induced by
high speed
high angles of attack.
large angles of yaw.
large angles of climb
7.
A normal shock wave
can occur at different points on the aeroplane in transonic flight.
is a discontinuity plane in an airflow, in which the temperature drops suddenly.
is a discontinuity plane in an airflow, which is always normal to the surface
is a discontinuity plane in an airflow, in which the pressure drops suddenly
8.
Which combination of design features is known to be responsible for deep stall?
Straight wings and a T-tail
Straight wings and aft fuselage mounted engines
Swept back wings and wing mounted engines
Swept back wings and a T-tail
9.
If an aeroplane is flying at transonic speed with increasing Mach number the shock wave on the upper side of the wing
moves into trailing edge direction
disappears.
moves into leading edge direction
stays all the time at the same position.
10.
Which of the following statements is true?
By increasing the flap setting in severe turbulence the stall speed will be reduced and the risk for exceeding the structural limits will be decreased
Through extension of the flaps in severe turbulence the centre of pressure will move aft which will increase the margins to the structural limits
Limiting factors in severe turbulence are the possibility of a stall and the margin to the structural limitations
Through extension of the flaps in severe turbulence it is possible to reduce the speed and increase the margins to the structural limits
11.
When the C.G. position is moved forward, the elevator deflection for a manoeuvre with a load factor greater than 1 will be
dependent on trim position
larger.
smaller.
unchanged
12.
What is the correct relation of the True Air Speed (TAS) for minimum sink rate (VR/Dmin) and best glide angle (VBest glide) at a given altitude?
VR/Dmin < VBest glide
VR/Dmin > VBest glide
VR/Dmin = VBest glide
VR/Dmin > VBest glide or VR/Dmin < VBest glide depending on the type of aeroplane.
13.
If the sum of moments in flight is not zero, the aeroplane will rotate about
the centre of pressure of the wing.
the neutral point of the aeroplane.
the centre of gravity
the aerodynamic centre of the wing
14.
The aspect ratio of the wing
is the ratio between the wing span and the mean geometric chord
is the ratio between the wing span and the root chord.
is the ratio between the tip chord and the wing span.
is the ratio between chord and root chord.
15.
A high aspect ratio wing produces
an increase in induced drag
a decrease in induced drag
less sensitivity to gust effects
a decrease in stall speed
16.
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 ?
the stick force per g decreases
the required lateral control force decreases
the required lateral control force increases.
the required lateral control force does not change
17.
Shock induced separation results in
decreasing lift
increasing lift.
decreasing drag
constant lift.
18.
Compared with stalling airspeed (VS) in a given configuration, the airspeed at which stick shaker will be triggered is
1.20 VS.
1.12 VS
1.30 VS.
greater than VS
19.
The loss of total pressure in a shock wave is due to the fact that
the friction in the boundary layer is higher.
the static pressure decrease is comparatively high.
the speed reduction is too high.
kinetic energy in the flow is changed into heat energy.
20.
The (1) stick force stability and the (2) manoeuvre stability are positively affected by
(1) aeroplane nose up trim (2) aeroplane nose up trim.
(1) forward C.G. position (2) forward CG. position
(1) aft C.G. position (2) aft CG. position.
(1) forward C.G. position (2) aeroplane nose up trim.
21.
Which of the following statements concerning control is correct?
In a differential aileron control system the control surfaces have a larger upward than downward maximum deflection
In general the maximum downward elevator deflection is larger than upward
Hydraulically powered control surfaces do not need mass balancing.
On some aeroplanes, the servo tab also serves as a trim tab.
22.
Which of the following statements about stall speed is correct ?
Increasing the anhedral of the wing will decrease the stall speed
Decreasing the angle of sweep of the wing will decrease the stall speed
Use of a T-tail will decrease the stall speed
Increasing the angle of sweep of the wing will decrease the stall speed.
23.
Which of these definitions of propeller parameters is correct?
Blade angle = angle between blade chord line and propeller axis
geometric propeller pitch = the theoretical distance a propeller blade element is travelling in forward direction in one propeller revolution
Propeller angle of attack = angle between blade chord line and propeller vertical plane
Critical tip velocity = propeller speed at which risk of flow separation at some parts of propeller blade occurs
24.
Increase of wing loading will
decrease the minimum gliding angle.
decrease take off speeds.
increase the stall speeds
increase CLmax
25.
The centre of gravity moving aft will
decrease the elevator up effectiveness
increase the elevator up effectiveness.
not affect the elevator up or down effectiveness
increase or decrease the elevator up effectiveness, depending on wing location.
26.
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
decrease and the rate of descent will increase.
increase and the rate of descent will increase.
increase and the rate of descent will decrease
decrease and the rate of descent will decrease
27.
Which statement is correct about a normal shock wave ?
The airflow changes from supersonic to subsonic
The airflow changes direction
The airflow expands when passing the aerofoil
The airflow changes from subsonic to supersonic
28.
A body is placed in a certain airstream. The density of the airstream decreases to half of the original value. The aerodynamic drag will decrease with a factor
1.4
4
2
8
29.
Which part of an aeroplane provides the greatest positive contribution to the static longitudinal stability ?
The fuselage
The engine
The horizontal tailplane.
The wing.
30.
On a non swept wing, when the aerofoil is accelerated from subsonic to supersonic speeds, the aerodynamic centre
remains unchanged
slightly shifts forward
shifts aft by about 10%.
shifts from 25% to about 50% of the aerofoil chord
31.
What is the purpose of an auto-slat system ?
ensures that the slats are always extended when the ground/flight system is in the ""ground"" position.
extend automatically when a certain value of angle of atttack is exceeded.
provide automatically slat IN selection after take-off.
assist the ailerons during rolling.
32.
Which formula or equation describes the relationship between force (F), acceleration (a) and mass (m)?
a=F. m
m=F.a
F=m / a
F=m. a
33.
Which of the following statements about the difference between Krueger flaps and slats is correct?
Deploying a slat will form a slot, deploying a Krueger flap does not.
Deploying a Krueger flap will increase critical angle of attack, deploying a slat does not.
Deploying a slat will increase critical angle of attack, deploying a Krueger flap does not
Deploying a Krueger flap will form a slot, deploying a slat does not.
34.
The Mach trim system will prevent
tuck under
shock stall.
dutch roll
buffeting.
35.
Vortex generators
reduce the spanwise flow on swept wing
transfer energy from the free airflow into the boundary layer.
take kinetic energy out of the boundary layer to reduce separation.
change the turbulent boundary layer into a laminar boundary layer
36.
The turn indicator shows a right turn. The slip indicator is left of neutral. To coordinate the turn
less right bank is required.
more right rudder is required
a higher turn rate is required.
more right bank is required
37.
In the transonic range lift will decrease at the shock stall due to the
appearance of the bow wave
separation of the boundary layer at the shock waves.
first appearance of a shock wave at the upper side of the wing
attachment of the shock wave on the trailing edge of the wing.
38.
The relative thickness of an aerofoil is expressed in
camber.
degrees cross section tail angle.
meters.
% chord
39.
A propeller turns to the right, seen from behind. The torque effect in the take-off will
roll the aeroplane to the right
pitch the aeroplane nose down
roll the aeroplane to the left.
pitch the aeroplane nose up
40.
The ""short period mode"" is an
oscillation about the vertical axis.
oscillation about the longitudinal axis
oscillation about the lateral axis
unstable movement of the aeroplane, induced by the pilot
41.
The term angle of attack in a two dimensional flow is defined as
the angle for maximum lift/drag ratio
the angle between the wing chord line and the direction of the relative wind/airflow
the angle between the aeroplane climb path and the horizon.
the angle formed by the longitudinal axis of the aeroplane and the chord line of the wing
42.
The normal stall recovery procedure for a light single engined aeroplane is
full power and stick roll-neutral nose-down, correction for angle of bank with stick.
full power and stick roll-neutral nose-down, correcting for angle of bank with rudder.
idle power and stick neutral, waiting for the natural nose-down tendency.
idle power and stick roll-neutral nose-down and no other corrections
43.
The max aft position of the centre of gravity is amongst others limited by the
too small effect of the controls on the aeroplane
minimum value of the stick force per g.
maximum elevator deflection
maximum longitudinal stability of the aeroplane
44.
When air has passed through a shock wave the speed of sound is
not affected
decreased.
decreased and beyond a certain Mach number start increasing again
increased.
45.
An aeroplane that has positive static stability
is never dynamically stable
is always dynamically stable.
is always dynamically unstable.
can be dynamically stable, neutral or unstable
46.
Vortex generators mounted on the upper wing surface will
increase the effectiveness of the spoiler due to increase in parasite drag.
decrease the shock wave induced separation
decrease the stalling speed by increase of the tangential velocity of the swept wing.
decrease the interference drag of the trailing edge flaps
47.
Why is a propeller blade twisted from root to tip?
To ensure that the tip produces most thrust.
To ensure that the root produces most thrust.
Because the local angle of attack of a blade segment is dependent on the ratio of that segment 's speed in the plane of rotation and the true airspeed of the aeroplane
Because the local angle of attack of a blade segment is dependent on the ratio of that segment 's speed in the plane of rotation and the angular velocity of the propellers
48.
What increases the stalling angle of attack ? Use of
slats
fuselage mounted speed-brakes
spoilers
flaps
49.
The stall speed increases, when: (all other factors of importance being constant)
pulling up from a dive
spoilers are selected from OUT to IN.
weight decreases
minor altitude changes occur e.g. 0-10.000 ft.
50.
The lift of an aeroplane of weight W in a constant linear climb with a climb angle (gamma) is approximately
W(1-tan.gamma).
W(1-sin.gamma).
W/cos.gamma
Wcos.gamma
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