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WorksheetsTechnical Quiz 1
Total questions: 50
Worksheet time: 25mins
The Influence of "Ground effect" is experienced by an aircraft when its height above the Ground is :-
About one wing span
About half wing span
About one and a half wing span
Dynamic pressure is equal to:
half the density times the indicated airspeed squared
half the true airspeed times the density squared
half the density times the true airspeed squared
Principle of continuity states, the mass flow is product of :-
Area, Pressure, density
Velocity, Area, density
Area, Velocity, Pressure
At zero angle of attack, the pressure along the upper surface of a symmetrical aerofoil section would be:
greater than atmospheric pressure.
equal to atmospheric pressure.
less than atmospheric pressure.
How can an aeroplane produce the same lift in ground effect as when out of ground effect?
A lower angle of attack.
A higher angle of attack.
The same angle of attack, but a lower IAS
Hazardous vortex turbulence that might be encountered behind large aircraft is created only when that aircraft is:
developing lift.
using high power settings.
operating at high airspeeds.
To avoid the wing tip vortices of a departing jet aeroplane during take-off, the pilot should:
climb above and stay upwind of the jet aeroplane's flight path.
lift off at a point well past the jet aeroplane's flight path.
remain below and downwind of the jet aeroplane's flight path.
What wind condition prolongs the hazards of wake turbulence on a landing runway for the longest period of time?
Light quartering headwind
Light quartering tailwind
Direct tailwind
For a symmetrical aerofoil, Centre of pressure moves:
Forward at increased AOA
Remains constant with change in AOA
Backward with increase in AOA
The angle of attack of a wing directly controls the:
distribution of pressures acting on the wing
amount of airflow above and below the wing.
dynamic pressure acting in the airflow.
Taper ratio is :-
Ratio of average chord to root chord
Ratio of root chord to tip chord
Ratio of tip chord to root chord
Choose the correct statement:
High performance seaplanes have high aspect ratio
Jet fighter aircraft have low aspect ratio
Both A and B
The aerodynamic centre is defined as:
The point on the wing MAC where the wing pitching moment does not vary with the lift coefficient
The point on the wing MAC where the wing pitching moment varies with the lift coefficient
The degree of positive camber has no effect on longitudinal stability
Choose incorrect statement, aspect ratio is
Ratio of wingspan to chord
Ratio of area to chord²
Ratio of area to span²
As per Bernoulli's theorem -
Decrease in speed along a stream line point decreases static pressure
Increase in speed at a point along stream line, Cause a decrease in static pressure at the point
Increase or Decrease in speed has no change in static pressure
Identity the following in ascending order :-
Chord line, MCL, Max Camber, Max Thickness
Chord line, MCL, Max Thickness, Max Camber
MCL Chord line, Max Camber, Max Thickness
Choose the correct :As an aircraft climbs out of ground effect the following changes takes place :-
The increase in downwash will produce a nose up pitching moment
The nose up pitching moment may induce an inadvertent over rotation and tail strike
Both A & B
On an aerofoil section, the force of lift acts perpendicular to, and the force of drag acts parallel to the;
flight path.
longitudinal axis.
chord line.
Choose the correct statement:
Decreasing the camber of an aerofoil will increase its lift
Increasing the camber of an aerofoil will increase its lift
Increasing the camber of an aerofoil will decrease its lift
Choose the correct statement for reducing induced drag
Having winglets
Shaping the wing tips
Both A and B
Lift and drag on airplane depend upon?
CP, CG, IAS, Air density
Angle of attack, air density, velocity, CG
Angle of attack, air density, aerofoil shape, velocity
Aircraft is at best L/D ratio when parasite drag is
At minimum
Is equal to induced drag
Greater than induced drag
Choose the correct statement for reducing induced drag
Having winglets
Shaping the wing tips
Both A and B
In modern aircraft L/D ratio is 10 and 20 to 1 which means?
Lift is 20 times drag is 10 times
Lift is 10 times drag is 3 times
Lift is 10 to 20 times greater than drag
The A/C is at best L/D ratio when parasite drag is ;
At minimum
Equal to induced drag
Greater than induced drag
In level flight, since lift equals weight, if the aircraft is performing a manoeuvre such that, life is twice the weight, the load factor will be:
1.5
4.0
2.0
Load factor is:
Weight divided by lift expressed as 'g'
CL divided by weight
Lift divided by weight expressed as 'g'
To avoid the wing tip vortices of a departing jet aeroplane during take-off, the pilot should:
climb above and stay upwind of the jet aeroplane's flight path.
lift off at a point well past the jet aeroplane's flight path.
remain below and downwind of the jet aeroplane's flight path.
Wing flaps extended speed (Vfe) is:
The minimum air speed at which the aircraft should be flown
The minimum airspeed at which the flaps can be extended and the aircraft can be flown.
The maximum air speed at which the aircraft should be flown with the flaps in a prescribed extended position.
If landing is made without flaps the landing speed must be:
Reduced
Increased
No change in speed is required
What is the effect of flaps during take-off and landing on ground effect
Decrease on ground effect
No effect
Increase on ground effect
Choose the correct statement:
High lift devices are fitted on leading edges only
High lift devices are fitted on trailing edges only
Can be fitted on leading and trailing edges.
How Centre of pressure moves with increase in AOA :-
Moves Forward
Moves Backward
Forward till 16° then backward
Stall speed does not depend on :-
lift and wing area
camber and air density
None of above
For asymmetrical aerofoil, lift starts producing at :-
0°
-2°
-4°
Which of following is not type of parasite drag :-
Skin friction
Interference drag
Induced drag
If the speed is tripled, what happens to induced drag and coefficient of induced drag ?
1/4 times and 1/16 times respectively
1/9 times and 1/27 times respectively
1/9 times and 1/81 times respectively
With increase of AOA, Transition point and separate point respectively:-
moves forward and backward
Both moves backward
Both moves forward
Foam drag is caused by :-
Pressure differential btw upper and lower surface of wing
Pressure differential btw infront and behind of wing
None of above
If an a/c is flying at a speed above ViMD, it lies in :-
Speed stable region
Speed unstable region
Speed neutral region
Power available is product of :-
Thrust and TAS
Thrust and IAS
Drag and TAS
Power required is proportional to :-
V²
V
V³
Choose the correct statement, Disadvantages of flaps :-
Steepens the glide angle without increasing the speed.
Lower stalling speed
Climb gradient decreased
At max excess power, an a/c gets :-
Max ROC and ViMD
Max ROC and 1.32 ViMD
Min ROC and 1.32 ViMD
If weight increases, ViMD :-
remain constant
increases
decreases
If the speed is doubled, the parasite drag is :-
constant
quadrupled
doubled
With increase in altitude, overall drag :-
reduces
increases
remains the same
Induced drag can be reduced by :-
Wing end plates
Winglet and Sharklets
Both A & B
Speed is inversely proportional to :
Induced drag
Lift
Both A & B
If an a/c is banking at an angle of 60°, the load factor is
0.2
0.5
2
