POF 101-150

On a wing, the force of lift acts perpendicular to, and the force of drag acts parallel to the:

• flight path.

• longitudinal axis.

• chord line.

• camber line

Which statement is true, regarding the opposing forces acting on an aeroplane in steady-state level flight?

• These forces are equal.

• Thrust is greater than drag and weight and lift are equal.

• Thrust is greater than drag and lift is greater than weight.

• Thrust is slightly greater than Lift, but the drag and weight are equal.

At higher elevation airports the pilot should know that indicated airspeed:

• will be unchanged, but ground speed will be faster.

• will be higher, but ground speed will be unchanged.

• should be increased to compensate for the thinner air.

• should be higher to obtain a higher landing speed.

An aeroplane leaving ground effect will:

• experience an increase in induced drag and require more thrust.

• require a lower angle of attack to maintain the same lift coefficient.

• experience a reduction in induced drag and require a smaller angle of attack

• experience a reduction in ground friction and require a slight power reduction

If the same angle of attack is maintained in ground effect as when out of ground effect, lift will:

• increase, and induced drag will decrease.

• increase, and induced drag will increase.

• decrease, and induced drag will increase.

• decrease and induced drag will decrease.

Which is true regarding the force of lift in steady, unaccelerated flight?

• There is a corresponding indicated airspeed required for every angle of attack to generate sufficient lift to maintain altitude.

• An aerofoil will always stall at the same indicated airspeed; therefore, an increase in weight will require an increase in speed to generate sufficient lift to maintain altitude.

• At lower airspeeds the angle of attack must be less to generate sufficient lift to maintain altitude.

• The lift force must be exactly equal to the drag force.

At a given Indicated Airspeed, what effect will an increase in air density have on lift and drag?

• Lift and drag will remain the same.

• Lift and drag will increase.

• Lift and drag will decrease.

• Lift will increase but drag will decrease.

If the angle of attack is increased beyond the critical angle of attack, the wing will no longer produce sufficient lift to support the weight of the aircraft:

• regardless of airspeed or pitch attitude.

• unless the airspeed is greater than the normal stall speed.

• unless the pitch attitude is on or below the natural horizon.

• in which case, the control column should be pulled back immediately.

Aspect ratio of the wing is defined as the ratio of the:

• wingspan to the average chord.

• square of the chord to the wingspan.

• wingspan to the wing root.

• square of the wing area to the span.

What changes to aircraft control must be made to maintain altitude while the airspeed is being decreased?

• Increase the angle of attack to compensate for the decreasing dynamic pressure.

• Maintain a constant angle of attack until the desired airspeed is reached, then increase the angle of attack.

• Increase angle of attack to produce more lift than weight.

• Decrease the angle of attack to compensate for the decrease in drag.