WorksheetsRPL Aerodynamics Section 1-8 Questions
Total questions: 24
Worksheet time: 12mins
When lift is developed it acts
Perpendicular to the chord line.
Perpendicular to the relative airflow.
Vertically.
Upwards and backwards.
At low airspeed and high power in a single-engine aeroplane
All controls are ‘sloppy’ ie less effective.
The ailerons remain effective, but the elevator and rudder are ‘sloppy’.
The elevator and rudder remain effective, but the ailerons become ‘sloppy’.
All controls remain as effective as at higher speeds.
Movement about the longitudinal axis is known as ________________
ROLL
YAW
PITCH
SPIN
Movement in the lateral plane ie about the normal axis is known as ________
ROLL
YAW
PITCH
SPIN
The aspect of ratio of a wing is defined as the ratio of
Lift to drag.
Span to chord.
Thickness to span.
Area to chord squared.
Bernoulli’s Principle says
Increased velocity in a streamline flow means decreased dynamic pressure.
Increased velocity in a streamline flow means decreased static pressure.
Increased velocity in a streamline flow means increased static pressure.
Dynamic and static pressure both remain constant in a streamline flow.
A secondary effect of aileron is
Yaw about the normal axis.
Roll about the normal axis.
Yaw about the longitudinal axis.
Roll about the longitudinal axis.
If the elevator trim tab is deflected up, which way will the aircraft’s nose move?
UP
DOWN
Slipstream effect is most noticeable
When full power is applied in normal light.
During a climbing turn to the right.
When full power is applied at a very low airspeed.
Only during the take-off roll.
In steady straight and level flight
Lift equals drag.
Lift equals weight.
Lift is greater than weight.
Thrust is greater than drag.
On a wing the force of lift acts perpendicular to and the force of drag parallel to
The chordline.
The longitudinal axis.
The relative airflow.
The lateral axis.
The Lift Formula is
L = CL1/2pV2
L = CL1/2pV S
L = CL1/2pV2 S
L = CL2/1pV2 S
The factors in the lift formula over which the pilot has control are
Angle of Attack
Airspeed
Angle of Attack
Air Density
Airspeed
RPM
Angle of Attack
Nose Attitude
As angle of attack is reduced from 16o to 0o, what will happen to the position of the centre of pressure and the amount of lift?
CoP moves Backwards
Lift Decreases
CoP moves Forwards
Lift Decreases
CoP doesn't move
Lift Decreases
CoP moves Backwards
Lift Increases
If the airspeed of an aeroplane is doubled in level flight the parasite drag will
Remain the same.
Decrease as airspeed increases.
Double.
Be four times greater.
As airspeed decreases in level flight below the speed for maximum L/D, total drag of an aeroplane will
Increase because of increasing induced drag.
Increase because of increasing parasite drag.
Decrease because of lower induced drag.
Decrease because of lower parasite drag.
The blade angle of a fixed-pitch propeller
Is greatest near the hub and decreases toward the tip.
Is least near the hub and greatest toward the tip.
Is the same at all points along the blade.
Is the greatest at the 75% station of the blade.
The most efficient angle of attack occurs
At the AoA giving the best L/D ratio.
At the AoA giving the best coefficient of lift.
At the AoA giving the least coefficient of lift.
At the stalling AoA.
What changes in the control of an aircraft must be made to maintain altitude when the airspeed is being decreased?
The AoA must remain the same.
The AoA must be increased to compensate for the decreasing lift caused by the reduction in airspeed.
The AoA must be increased to produce more lift than weight.
The AoA must be decreased.
The reason that some aeroplanes tend to drop their nose during power reduction is
The thrust line is above the drag line.
The thrust line and the drag line are the same.
The centre of pressure is ahead of the centre of gravity.
The thrust line is below the drag line.
At low airspeeds
Total drag is the same as at all other speeds.
Total drag is less than at any higher speed.
Total drag increases due to increased induced drag.
Total drag increases due to increased parasite drag.
At high airspeeds
Total drag increases due to increased parasite drag.
Total drag increases due to increased induced drag.
Total drag decreases.
Total drag remains the same as at all other airspeeds.
Lowering the flaps will
Increase lift and decrease drag.
Increase lift and increase drag.
Decrease lift and decrease drag.
Decrease lift and increase drag.
The pilot can change the value of the coefficient of lift by
Increasing power.
Altering the AoA with the elevator.
Decreasing speed.
The coefficient of lift is fixed for a given aerofoil; it cannot be changed by the pilot.
