a2222

An aircraft is travelling at a speed of 720 nautical miles per hour. To calculate speed in MPH you.

• divide by 0.83.

• multipy by 0.83.

• multiply by 1.15.

Lift on a delta wing aircraft.

• increases with an increased angle of incidence (angle of attack).

• does not change with a change in angle of incidence (angle of attack).

• decreases with an increase in angle of incidence (angle of attack).

The CofP is the point where.

• the lift can be said to act.

• the three axis of rotation meet.

• all the forces on an aircraft act.

When an aircraft experiences induced drag.

• air flows under the wing span wise towards the root and on top of the wing span wise towards the tip.

• Neither a) or b) since induced drag does not caused by span wise flow.

• air flows under the wing span wise towards the tip and on top of the wing span wise towards the root.

At stall, the wingtip stagnation point.

• doesn’t move.

• moves toward the lower surface of the wing.

• moves toward the upper surface of the wing.

The rigging angle of incidence of an elevator is.

• the angle between the bottom surface of the elevator and the longitudinal datum.

• the angle between the bottom surface of the elevator and the horizontal in the rigging position.

• the angle between the mean chord line and the horizontal in the rigging position.

Which of the following is true?.

• Lift acts at right angles to the relative airflow and weight acts vertically down.

• Lift acts at right angles to the wing chord line and weight acts vertically down.

• Lift acts at right angles to the relative air flow and weight acts at right angles to the aircraft centre line.

The vertical fin of a single engined aircraft is.

• parallel with the longitudinal axis but not the vertical axis.

• parallel with both the longitudinal axis and vertical axis.

• parallel with the vertical axis but not the longitudinal axis.

"What happens to air flowing at the speed of sound

when it enters a converging duct?."

• Velocity increases, pressure and density decreases.

• Velocity, pressure and density increase.

• Velocity decreases, pressure and density increase.

As the angle of attack of an airfoil increases the centre of pressure.

• remains stationary.

• moves aft.

• moves forward.