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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 total drag vary as speed is increased from stalling speed (VS) to maximum IAS (VNE) in a straight and level flight at constant weight?
Decreasing, then increasing
Increasing
Decreasing
Increasing, then decreasing.
2.
In a turn, the load factor n and the stalling speed VS will be
n greater than 1, VS lower than in straight and level flight.
n smaller than 1, VS higher than in straight and level flight.
n greater than 1, VS higher than in straight and level flight
n smaller than 1, VS lower than in straight and level flight
3.
Differential aileron deflection
is required to achieve the required roll-rate.
increases the CLmax
is required to keep the total lift constant when ailerons are deflected.
equals the drag of the right and left aileron
4.
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)
remain the same
decrease.
increase.
increase or decrease, depending on the initial angle of attack.
5.
In the transonic range the aeroplane characteristics are strongly determined by
the CAS.
the IAS.
the Mach Number
the TAS
6.
For a fixed-pitch propeller designed for cruise, the angle of attack of each blade, measured at the reference section
is optimum when the aircraft is in a stabilized cruising flight
decreases when the aircraft speed decreases (with identical engine RPM).
is lower in ground run than in flight (with identical engine RPM).
is always positive during idling descent
7.
Which one of the following statements about the lift-to-drag ratio in straight and level flight is correct?
At the highest value of the lift/drag ratio the total drag is lowest
The highest value of the lift/drag ratio is reached when the lift is equal to the aircraft weight
The lift/drag ratio always increases as the lift decreases
The highest value of the lift/drag ratio is reached when the lift is zero.
8.
When an aeroplane with the centre of gravity forward of the centre of pressure of the combined wing / fuselage is in straight and level flight, the vertical load on the tailplane will be
upwards.
downwards because it is always negative regardless of the position of the centre of gravity.
zero because in steady flight all loads are in equilibrium.
downwards.
9.
Vortex generators mounted on the upper wing surface will
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
increase the effectiveness of the spoiler due to increase in parasite drag.
10.
After the transition point between the laminar and turbulent boundary layer
the boundary layer gets thinner and the speed increases
the boundary layer gets thicker and the speed decreases
the mean speed and friction drag increases
the mean speed increases and the friction drag decreases
11.
The function of the stick pusher is
to activate and push the stick forward prior to stick shaker
to vibrate the controls
to activate and push the stick forward at or beyond a certain value of angle of attack.
to pull the stick, to avoid a high speed stall
12.
The maximum acceptable cruising altitude is limited by a minimum acceptable loadfactor because exceeding that altitude
Mach buffet will occur immediately.
turbulence may induce Mach buffet
a sudden necessary bankangle may exceed the limit load factor.
turbulence may exceed the limit load factor
13.
Which statement is correct about a normal shock wave ?
The airflow changes direction
The airflow expands when passing the aerofoil
The airflow changes from supersonic to subsonic
The airflow changes from subsonic to supersonic
14.
The stall speed
increases with an increased weight
decreases with an increased weight
does not depend on weight
increases with the length of the wingspan
15.
What is the effect on the aeroplane's static longitudinal stability of a shift of the centre of gravity to a more aft location and on the required control deflection for a certain pitch up or down?
The static longitudinal stability is larger and the required control deflection is smaller.
The static longitudinal stability is larger and the required control deflection is larger
The static longitudinal stability is smaller and the required control deflection is smaller
The static longitudinal stability is smaller and the required control deflection is larger
16.
A deployed slat will
decrease the boundary layer energy and decrease the suction peak on the slat, so that CLmax is reached at lower angles of attack.
increase the boundary layer energy, move the suction peak from the fixed part of the wing to the slat, so that the stall is postponed to higher angles of attack.
increase the camber of the aerofoil and increase the effective angle of attack, so that CLmax is reached at higher angles of attack.
increase the boundary layer energy and increase the suction peak on the fixed part of the wing, so that the stall is postponed to higher angles of attack.
17.
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)
move aft
move forward
remain unaffected
remain matching the airfoil aerodynamic centre
18.
""Flutter"" may be caused by
low airspeed aerodynamic wing stall.
roll control reversal
distorsion by bending and torsion of the structure causing increasing vibration in the resonance frequency
high airspeed aerodynamic wing stall
19.
Which of the following statements about stall speed is correct ?
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 anhedral of the wing will decrease the stall speed
Increasing the angle of sweep of the wing will decrease the stall speed.
20.
The aspect ratio of the wing
is the ratio between chord and root chord.
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.
21.
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
decrease and the rate of descent will increase
decrease and the rate of descent will decrease
increase and the rate of descent will increase
increase and the rate of descent will decrease
22.
During an erect spin recovery
the control stick is moved side ways, in the direction of the angle of bank
the control stick is pulled to the most aft position
the ailerons are held in the neutral position
the control stick is moved side ways, against the angle of bank.
23.
An aeroplane that has positive static stability
is always dynamically unstable.
is always dynamically stable.
can be dynamically stable, neutral or unstable
is never dynamically stable
24.
A jet aeroplane equipped with inboard and outboard ailerons is cruising at its normal cruise Mach number. In this case
only the spoilers will be active, not the ailerons
the inboard and outboard ailerons are active
only the inboard ailerons are active.
only the outboard aileron are active
25.
How is adverse yaw compensated for during entry into and roll out from a turn ?
Horn-balanced controls
Servo tabs
Anti-balanced rudder control
Differential aileron deflection
26.
Which of the following factors will lead to an increase of ground distance during a glide ?
tailwind
headwind
decrease of aeroplane weight
increase of aeroplane weight
27.
Mcrit is the free stream Mach Number at which
the critical angle of attack is reached
somewhere about the airframe Mach 1 is reached locally
shockstall occurs
Mach buffet occurs.
28.
A horn balance in a control system has the following purpose
to prevent flutter
to decrease the effective longitudinal dihedral of the aeroplane
to decrease stick forces.
to obtain mass balancing.
29.
An aeroplane has static directional stability, in a side-slip to the right, initially the
right wing tends to go down.
nose of the aeroplane will remain in the same direction
nose of the aeroplane tends to move to the right.
nose of the aeroplane tends to move to the left
30.
How does the exterior view of an aeroplane change, when the trim is used during a speed decrease ?
Nothing changes in the exterior view
The elevator is deflected further downwards by means of an upwards deflected trimtab
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.
31.
Which is one of the disadvantages of increasing the number of propeller blades ?
decrease propeller efficiency
Increased noise
Higher tip-speed
Less power can be absorbed by the propeller
32.
Which of the following flight phenomena can only happen at Mach Numbers above the critical Mach Number?
Dutch roll
Speed instability
Mach buffet
Elevator stall
33.
When the air is passing through a shock wave the density will
stay constant
decrease and beyond a certain Mach number start increasing again
increase.
decrease.
34.
If an aeroplane flies in the ground effect
the effective angle of attack is decreased.
the induced angle of attack is increased
drag and lift are reduced.
the lift is increased and the drag is decreased.
35.
""Tuck under"" is
the tendency to nose down when speed is increased into the transonic flight regime
shaking of the control column at high Mach Number
the tendency to nose down when the control column is pulled back.
the tendency to nose up when speed is increased into the transonic flight regime
36.
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
37.
When the air is passing through an expansion wave the static temperature will
decrease and beyond a certain Mach number start increasing again
decrease.
stay constant
increase.
38.
One method to compensate adverse yaw is a
balance panel
antibalance tab.
balance tab
differential aileron
39.
Which kind of boundary layer has the strongest change in velocity close to the surface?
Laminar boundary layer
Transition boundary layer
Turbulent boundary layer
No difference
40.
If you decrease the propeller pitch during a glide with idle-power at constant IAS the lift to drag ratio will
increase and the rate of descent will decrease
decrease and the rate of descent will decrease.
increase and the rate of descent will increase
decrease and the rate of descent will increase
41.
At what speed does the front of a shock wave move across the earth's surface?
The true air speed of the aeroplane.
The ground speed of the aeroplane
The speed of sound at ground level
The speed of sound at flight level
42.
Which one of the following statements about the dynamic stability of a conventional aeroplane about the lateral axis is correct?
Speed remains constant during one period of the phugoid.
An aft C.G. position shortens the period time of the phugoid.
Period time of the phugoid is normally 5 sec
Damping of the phugoid is normally very weak
43.
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
44.
The consequences of exceeding Mcrit in a swept-wing aeroplane may be : (assume no corrective devices, straight and level flight)
buffeting of the aeroplane and a tendency to pitch down
an increase in speed and a tendency to pitch up.
buffeting of the aeroplane and a tendency to pitch up.
engine unbalance and buffeting.
45.
The unit of measurement of pressure is
kg/m³
kg/dm²
psi
b/gal
46.
Just above the critical Mach number the first evidence of a shock wave will appear at the
trailing edge of the wing
lower side of the wing.
upper side of the wing.
leading edge of the wing
47.
The aerofoil polar is
a graph of the relation between the lift coefficient and the angle of attack.
a graph, in which the thickness of the wing aerofoil is given as a function of the chord.
a graph of the relation between the lift coefficient and the drag coefficient
the relation between the horizontal and the vertical speed
48.
A propeller is turning to the right, seen from behind. The asymmetric thrust effect is mainly induced by
large angles of yaw.
large angles of climb
high speed
high angles of attack.
49.
Low speed pitch up is caused by the
wing tip vortex
spanwise flow on a swept back wing.
spanwise flow on a swept forward wing
Mach trim system
50.
The induced drag
increases as the lift coefficient increases
has no relation to the lift coefficient
increases as the aspect ratio increases
increases as the magnitude of the tip vortices decreases
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