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CPL Test Series
Question Bank
Questions for INDIGO AERODYNAMIC 5259-5689
Answer the following questions
Test Mode
Training Mode
1.
How does the exterior view of an aeroplane change, when the trim is used during a speed decrease ?
The elevator is deflected further upwards by means of a downwards deflected trimtab.
The elevator is deflected further downwards by means of a trimmable horizontal stabiliser.
The elevator is deflected further downwards by means of an upwards deflected trimtab
Nothing changes in the exterior view
2.
The manoeuvrability of an aeroplane is best when the
speed is low
C.G. position is on the forward C.G. limit
flaps are down
C.G. is on the aft C.G. limit
3.
Increase of wing loading will
decrease take off speeds.
decrease the minimum gliding angle.
increase CLmax
increase the stall speeds
4.
The regime of flight from the critical Mach number up to M = 1.3 is called the
supersonic range
hypersonic range
subsonic range
transonic range
5.
Which of the following statements about stall speed is correct ?
Decreasing the angle of sweep of the wing will decrease the stall speed
Increasing the anhedral 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.
6.
The induced drag
has no relation to the lift coefficient
increases as the lift coefficient increases
increases as the aspect ratio increases
increases as the magnitude of the tip vortices decreases
7.
The buffet margin
increases during a descent with a constant IAS.
decreases during a descent with a constant Mach number.
is always positive at Mach numbers below MMO.
is always greatest after a stepclimb has been executed
8.
Dihedral of the wing
is only positive for aeroplanes with high mounted wings.
decreases the static lateral stability.
increases the static lateral stability
is the only way to increase the static lateral stability
9.
The trailing edge flaps when extended
significantly increase the angle of attack for maximum lift
increase the zero lift angle of attack
worsen the best angle of glide
significantly lower the drag
10.
During an erect spin recovery
the control stick is moved side ways, against the angle of bank.
the ailerons are held in the neutral position
the control stick is pulled to the most aft position
the control stick is moved side ways, in the direction of the angle of bank
11.
Considering a positive cambered aerofoil, the pitch moment when Cl=0 is
positive (pitch-up).
negative (pitch-down).
equal to zero.
infinite
12.
How does stalling speed (IAS) vary with altitude?
It increases with increasing altitude, because the density decreases.
It remains constant at lower altitudes but increases at higher altitudes due to compressibility effects
It remains constant at lower altitudes but decreases at higher altitudes due to compressibility effects.
It remains constant
13.
An aeroplane has a stall speed of 100 kt at a load factor n=1. In a turn with a load factor of n=2, the stall speed is
141 kt
200 kt
282 kt
70 kt
14.
An aeroplane has a servo-tab controlled elevator. What will happen when only the elevator jams during flight ?
Pitch control reverses direction
The pitch control forces double
The servo-tab now works as a negative trim-tab.
Pitch control has been lost
15.
If you increase the propeller pitch during a glide with idle-power at constant IAS the lift to drag ratio 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
16.
An aeroplane with swept back wings is equipped with slats and/or leading edge (L.E.) flaps. One possible efficient way to arrange the leading edge devices on the wings is
Wing roots: slatsWing tips: no devices
Wing roots: L.E. flapsWing tips: slats
Wing roots: L.E. flapsWing tips: no devices
Wing roots: slatsWing tips: L.E. flaps
17.
The loss of total pressure in a shock wave is due to the fact that
the static pressure decrease is comparatively high.
kinetic energy in the flow is changed into heat energy.
the speed reduction is too high.
the friction in the boundary layer is higher.
18.
The ""short period mode"" is an
unstable movement of the aeroplane, induced by the pilot
oscillation about the longitudinal axis
oscillation about the lateral axis
oscillation about the vertical axis.
19.
Why is VMCG determined with the nosewheel steering disconnected?
Because the value of VMCG must also be applicable on wet and/or slippery runways
Because nosewheel steering has no effect on the value of VMCG
Because it must be possible to abort the take-off even after the nosewheel has already been lifted off the ground
Because the nosewheel steering could become inoperative after an engine has failed.
20.
Flap selection at constant IAS in straight and level flight will increase the
lift and the drag
lift coefficient and the drag
maximum lift coefficient (CLmax) and the drag
stall speed
21.
For an aeroplane with one fixed value of VA the following applies. VA is
just another symbol for the rough air speed
the maximum speed in smooth air
the speed at which unrestricted application of elevator control can be used, without exceeding the maximum manoeuvring limit load factor
the speed at which the aeroplane stalls at the manoeuvring limit load factor at MTOW
22.
Which of the following wing planforms produces the lowest induced drag? (all other relevant factors constant)
Tapered.
Elliptical.
Rectangular.
Circular.
23.
To be able to predict compressibility effects you have to determine the
TAS.
Mach Number
EAS.
IAS.
24.
If the sum of moments in flight is not zero, the aeroplane will rotate about
the centre of gravity
the neutral point of the aeroplane.
the centre of pressure of the wing.
the aerodynamic centre of the wing
25.
Which statement about a primary control surface controlled by a servo tab, is correct ?
Due to the effectiveness of the servo tab the control surface area can be smaller
The servo tab can also be used as a trimtab
The control effectiveness of the primary surface is increased by servo tab deflection
The position is undetermined during taxiing, in particular with tailwind
26.
The value of the parasite drag in straight and level flight at constant weight varies linearly with the
square of the angle of attack.
angle of attack
square of the speed
speed.
27.
In the transonic range the aeroplane characteristics are strongly determined by
the IAS.
the Mach Number
the TAS
the CAS.
28.
The critical Mach number for an aerofoil equals the free stream airfoil Mach number at which
a ""supersonic bell"" appears on the upper surface
sonic speed (M=1) is reached at a certain point on the upper side of the aerofoil
a shock-wave appears on the upper surface
a shock-wave appears on the upper surface
29.
A propeller is turning to the right, seen from behind. The asymmetric thrust effect is mainly induced by
high speed
large angles of climb
high angles of attack.
large angles of yaw.
30.
The unit of measurement of pressure is
kg/m³
psi
b/gal
kg/dm²
31.
When the air is passing through an expansion wave the local speed of sound will
increase.
decrease.
stay constant
decrease and beyond a certain Mach number start increasing again.
32.
The term angle of attack in a two dimensional flow is defined as
the angle formed by the longitudinal axis of the aeroplane and the chord line of the wing
the angle between the wing chord line and the direction of the relative wind/airflow
the angle for maximum lift/drag ratio
the angle between the aeroplane climb path and the horizon.
33.
Which of these definitions of propeller parameters is correct?
Blade angle = angle between blade chord line and propeller axis
Propeller angle of attack = angle between blade chord line and propeller vertical plane
geometric propeller pitch = the theoretical distance a propeller blade element is travelling in forward direction in one propeller revolution
Critical tip velocity = propeller speed at which risk of flow separation at some parts of propeller blade occurs
34.
The unit of density is
psi
kg/cm²
Bar
kg/m³
35.
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
beneath to the top of the wing via the wing tip
the top to beneath the wing via the leading edge
the top to beneath the wing via the wing's trailing edge
beneath to the top of the wing via the trailing edge
36.
In a twin-engined jet powered aeroplane (engines mounted below the low wings) the thrust is suddenly increased. Which elevator deflection will be required to maintain the pitching moment zero ?
No elevator movement will required because the thrust line of the engines remains unchanged
Down.
It depends on the position of the centre of gravity
Up.
37.
A light twin is in a turn at 20 degrees bank and 150 kt TAS. A more heavy aeroplane at the same bank and the same speed will
turn at the same turn radius
turn at a smaller turn radius.
turn at a bigger turn radius
turn at a higher turn rate
38.
The terms ""q"" and ""S"" in the lift formula are
dynamic pressure and the area of the wing
square root of surface and wing loading
static pressure and dynamic pressure
static pressure and wing surface area
39.
The lift coefficient (CL) of an aeroplane in steady horizontal flight is 0.42, increase in angle of attack of 1 degree increases CL by is 0.1. A vertical up gust instantly changes the angle of attack by 3 degrees. The load factor will be
2.49
0.74
1.49
1.71
40.
Shock induced separation results in
constant lift.
decreasing lift
increasing lift.
decreasing drag
41.
Mcrit is the free stream Mach Number at which
somewhere about the airframe Mach 1 is reached locally
the critical angle of attack is reached
shockstall occurs
Mach buffet occurs.
42.
The relative thickness of an aerofoil is expressed in
degrees cross section tail angle.
% chord
camber.
meters.
43.
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)
increase.
remain the same
decrease.
increase or decrease, depending on the initial angle of attack.
44.
A boundary layer fence on a swept wing will
improve the high speed characteristics
increase the critical Mach Number
improve the low speed characteristics
improve the lift coefficient of the trailing edge flap
45.
Climbing at a constant Mach Number up to FL 350 the TAS will
decrease.
remain constant
increase.
first increase, then decrease.
46.
What is the unit of measurement for power ?
Nm/s
N/m
Pa/m²
kgm/s²
47.
Tuck under will happen
only below the critical Mach number
only at the critical Mach number
only above the critical Mach number
above or below the critical Mach number depending on the angle of attack
48.
If the altitude is increased and the TAS remains constant in the standard troposphere the Mach Number will
increase.
increase or decrease, depends of the type of aeroplane
not change.
decrease.
49.
Gyroscopic precession of the propeller is induced by
increasing RPM and yawing.
increasing RPM and rolling
pitching and rolling
pitching and yawing
50.
What is the influence of decreasing aeroplane weight on Mcrit at constant IAS ?
Mcrit decreases as a result of flying at a greater angle of attack.
Mcrit decreases
Mcrit increases as a result of compressibility effects
Mcrit increases as a result of flying at a smaller angle of attack
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