Module 8 Set 1 AST

The ISA value for air density is calculated by

Steady state airflow around a cylindrical body becomes turbulent at the

Airflow velocities around a body may be calculated using

The result of ice forming on an aero plane wing in flight will be, increase in weight and

According to Lapse Rate theory, if sea level temperature is 10’C temperature

Equivalent airspeed is calculated by multiplying calibrated airspeed by the ratio of

On a conventional aero foil section, as angle of attack is increased, the

Total drag on an aero plane in flight is greater than the sum of lift dependent drag, skin friction and form drag because of

To maintain the same altitude when velocity is increased

The most efficient angle of attack for an aero foil may be obtained by referring to the

The total drag of a symmetrical aero foil at zero angle of attack is made up of

When a aircraft in straight and level flight suffers an engine failure, the transition to a stable glide is due to the

In a stable climb, the rate of climb is proportional to the amount by which

When an aero plane is in a stable glide, if the pilot reduces the angle of attack, speed will

In a turn, if bank angle is increased, lift

In a turn during which a force of 2G is produced, the aero plane's stalling speed will be the

If two identical aero planes with a large difference in their weight are stalled

The lift generated by a general-purpose aero foil would be ‘zero’ at

Longitudinal dihedral is the angle between the

When an aero foil stalls, the movement of the center of pressure will cause the