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CPL Test Series
Question Bank
Questions for INDIGO AERODYNAMIC 5259-5689
Answer the following questions
Test Mode
Training Mode
1.
Entering the stall the centre of pressure of a straight (1) wing and of a strongly swept back wing (2) will
(1) move aft, (2) not move.
(1) not move (2) move forward
(1) move aft, (2) move forward.
(1) move aft, (2) move aft.
2.
The use of a slot in the leading edge of the wing enables the aeroplane to fly at a slower speed because
it changes the camber of the wing
the laminar part of the boundary layer gets thicker
it decelerates the upper surface boundary layer air
it delays the stall to a higher angle of attack
3.
When the air has passed through a normal shock wave the Mach number is
equal to 1.
lower than before but still greater than 1.
less than 1.
higher than before
4.
When the trailing edge flaps are deflected in level flight, the change in pitch moment will be
nose up
dependent on c.g. location
zero.
nose down
5.
""A line connecting the leading- and trailing edge midway between the upper and lower surface of a aerofoil"". This definition is applicable for
the camber line
the upper camber line
the chord line
the mean aerodynamic chord line
6.
Which type of wing arrangement decreases the static lateral stability of an aeroplane?
Dihedral.
Anhedral.
High wing
Increased wing span
7.
Which moments or motions interact in a dutch roll?
Pitching and yawing
Pitching and adverse yaw.
Rolling and yawing
Pitching and rolling
8.
The critical Mach number for an aerofoil equals the free stream airfoil Mach number at which
a ""supersonic bell"" appears on the upper surface
a shock-wave appears on the upper surface
a shock-wave appears on the upper surface
sonic speed (M=1) is reached at a certain point on the upper side of the aerofoil
9.
On a swept wing aeroplane at low airspeed, the ""pitch up"" phenomenon
is caused by boundary layer fences mounted on the wings
is caused by extension of trailing edge lift augmentation devices
is caused by wingtip stall.
never occurs, since a swept wing is a ""remedy"" to pitch up
10.
An aeroplane is in a steady turn, at a constant TAS of 300 kt, and a bank angle of 45°. Its turning radius is equal to:(given: g= 10 m/s²)
4743 metres
2381 metres
9000 metres
3354 metres
11.
In case the Mach trimmer fails
the aeroplane weight must be limited.
the Mach number must be limited.
the speed must be kept constant
try to relocate the centre-of-gravity aft.
12.
At higher altitudes, the stall speed (IAS)
decreases until the tropopause
decreases
increases
remains the same
13.
On a symmetrical aerofoil, the pitch moment for which Cl=0 is
positive (pitch-up)
equal to the moment coefficient for stabilized angle of attack
zero
negative (pitch-down)
14.
Which of the following statements about dihedral is correct?
The ""effective dihedral"" of an aeroplane component means the contribution of that component to the static lateral stability
Dihedral contributes to dynamic but not to static lateral stability
Effective dihedral is the angle between the 1/4-chord line and the lateral axis of the aeroplane
Dihedral is necessary for the execution of slip-free turns
15.
VMO
is the calibrated airspeed at which MMO is reached at 35 000 ft.
is equal to the design speed for maximum gust intensity
should be not greater than VC.
should be chosen in between VC and VD
16.
A strongly swept back wing stalls. If the wake of the wing contacts the horizontal tail, the effect on the stall behaviour can be
nose up tendency and/or lack of elevator response
tendency to increase speed after initial stall
increase sensitivity of elevator inputs
nose down tendency
17.
Longitudinal static stability is created by the fact that the
aeroplane possesses a large trim speed range.
centre of gravity is located in front of the leading edge of the wing
centre of gravity is located in front of the neutral point of the aeroplane
wing surface is greater than the horizontal tail surface
18.
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
downwards.
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.
upwards.
19.
In transonic flight the ailerons will be less effective than in subsonic flight because
aileron deflection only affects the air in front of the shock wave.
behind the shock wave pressure is lower
aileron down deflection moves the shock wave forward
aileron deflection only partly affects the pressure distribution around the wing
20.
When an aeroplane is flying through the transonic range with increasing Mach Number the centre of the pressure of the wing will move aft. This requires
a higher IAS to compensate the nose down effect.
a stability augmentation system.
a pitch up input of the stabilizer.
much more thrust from the engine
21.
The unit of density is
Bar
kg/m³
psi
kg/cm²
22.
What data may be obtained from the Buffet Onset Boundary chart?
The values of Mcrit at different weights and altitudes
The values of MMO at different weights and altitudes
The values of the Mach Number at which low speed and Mach Buffet occur at different weights and altitudes
The values of the Mach Number at which low speed and shock-stall occur at different weights and altitudes.
23.
The location of the centre of pressure of a positive cambered wing at increasing angle of attack will
not shift.
shift forward
shift in spanwise direction.
shift aft.
24.
The positive manoeuvring limit load factor for a large jet transport aeroplane with flaps extended is
3.75
2.0
2.5
1.5
25.
If you increase 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 increase.
increase and the rate of descent will decrease
decrease and the rate of descent will increase
decrease and the rate of descent will decrease
26.
Which of the following (1) aerofoils and (2) angles of attack will produce the lowest Mcrit values?
(1) thick and (2) large.
(1) thick and (2) small.
(1) thin and (2) large
(1) thin and (2) small.
27.
What is the effect of high aspect ratio of an aeroplane's wing on induced drag?
It is reduced because the effect of wing-tip vortices is reduced.
It is unaffected because there is no relation between aspect ratio and induced drag.
It is increased because high aspect ratio has greater frontal area
It is increased because high aspect ratio produces greater downwash.
28.
Compared with an oblique shock wave at the same Mach number a normal shock wave has a
higher total pressure
lower static temperature
higher loss in total pressure
higher total temperature
29.
A slotted flap will increase the CLmax by
increasing the camber of the aerofoil and improving the boundary layer
increasing only the camber of the aerofoil.
decreasing the skin friction
increasing the critical angle of attack
30.
What is the most effective flap system?
Split flap.
Single slotted flap
Fowler flap
Plain flap
31.
The max aft position of the centre of gravity is amongst others limited by the
maximum longitudinal stability of the aeroplane
minimum value of the stick force per g.
too small effect of the controls on the aeroplane
maximum elevator deflection
32.
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 larger
The static longitudinal stability is smaller 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 larger and the required control deflection is smaller.
33.
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
34.
When power assisted controls are used for pitch control, this
can only function in combination with an elevator trim tab.
makes aerodynamic balancing of the control surfaces meaningless
makes trimming superfluous
ensures that a part of the aerodynamic forces is still felt on the column
35.
The lift force, acting on an aerofoil
increases, proportional to the angle of attack until 40 degrees.
is maximum at an angle of attack of 2 degrees
is mainly caused by suction on the upperside of the aerofoil.
is mainly caused by overpressure at the underside of the aerofoil
36.
Which of the following lists aeroplane features that each increase static lateral stability ?
Sweep back, under wing mounted engines, winglets.
Low wing, dihedral, elliptical wing planform.
High wing, sweep back, large and high vertical fin
Fuselage mounted engines, dihedral, T-tail
37.
Which statement is correct about the laminar and turbulent boundary layer
separation point will occur earlier in the turbulent layer
friction drag will be equal in both types of layers
friction drag is lower in the turbulent layer
friction drag is lower in the laminar layer
38.
The total pressure is
can be measured in a small hole in a surface, parallel to the local stream.
static pressure minus the dynamic pressure
½ rho V²
static pressure plus the dynamic pressure
39.
Dihedral of the wing
is only positive for aeroplanes with high mounted wings.
increases the static lateral stability
is the only way to increase the static lateral stability
decreases the static lateral stability.
40.
Slat extension will
decrease the energy in the boundary layer on the upperside of the wing
increase critical angle of attack.
create gaps between leading edge and engine nacelles.
increase critical angle of attack.
41.
The critical Mach Number of an aeroplane can be increased by
sweep back of the wings
control deflection
vortex generators
dihedral of the wings.
42.
How does stalling speed (IAS) vary with altitude?
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 increases with increasing altitude, because the density decreases.
It remains constant
43.
The (1) stick force stability and the (2) manoeuvre stability are positively affected by
(1) forward C.G. position (2) forward CG. position
(1) aeroplane nose up trim (2) aeroplane nose up trim.
(1) aft C.G. position (2) aft CG. position.
(1) forward C.G. position (2) aeroplane nose up trim.
44.
Upon extension of a spoiler on a wing
CD is increased and CL is decreased
both CL and CD are increased
only CL is decreased (CD remains unaffected).
CD is increased, while CL remains unaffected.
45.
What factors determine the distance travelled over the ground of an aeroplane in a glide ?
The wind and the lift/drag ratio, which changes with angle of attack
The wind and the aeroplane's mass
The wind and CLmax
The wind and weight together with power loading, which is the ratio of power output to the weight
46.
During flap down selection in a continuous straight and level flight at constant IAS and weight
the stall speed increases
the centre of pressure moves aft
the total boundary layer becomes laminar
the lift coefficient and the drag coefficient increase.
47.
If the elevator trim tab is deflected up, the cockpit trim indicator presents
nose-up
neutral.
nose-down.
nose-left.
48.
One method to compensate adverse yaw is a
balance panel
differential aileron
balance tab
antibalance tab.
49.
Which statement is correct?
Extension of flaps will increase (CL/CD)max, causing the minimum rate of descent to decrease.
Extension of flaps has no influence on the minimum rate of descent, as only the TAS has to be taken into account
Extension of flaps causes a reduction of the stall speed, the maximum glide distance also reduces
Spoiler extension decreases the stall speed and the minimum rate of descent, but increases the minimum descent angle
50.
The lift coefficient (CL) of an aeroplane in steady horizontal flight is 0.4. Increase of 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
2.0
3.18
2.13
1.09
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