Stalling and Spinning

Question 1

The critical angle of attack for subsonic aerofoils is?

Answer 1

15 degrees

Question 2

The airflow strikes the leading edge and is momentarily brought to rest, this is known as the?

Answer 2

stagnation point

Question 3

The point where laminar flow becomes turbulent is know as the?

Answer 3

transition point

Question 4

The point where airflow closest to the aerofoil reverse directions is called?

Answer 4

the separation point

Question 5

For a conventional tailplane, applying flaps may?

Answer 5

Reduce stall buffet, since the downwash will be altered

Question 6

Vs =

Answer 6

square root of (weight / CL(max) 1/2 p S)

Question 7

The stall will occur at the same indicated airspeed irrespective of?

Answer 7

Altitude

Question 8

A progressive reduction of wing incidence from the root to the tip, to delay a wing tip stall, is called?

Answer 8

Washout

Question 9

Comparing high aspect ratio to low aspect ratio wings, which have better root stalling characteristics?

Answer 9

Low aspect ratio wings

Question 10

Short, but wide wings, are?

Answer 10

Low aspect ratio wings

Question 11

Long, but narrow wings are?

Answer 11

high aspect ratio wings

Question 12

Between tapered and rectangular wings, which has better root stall characteristics?

Answer 12

The rectangular wing

Question 13

Flaps reduce the?

Answer 13

Stalling angle

Question 14

Why does flaps reduce the stalling angle, or the angle at which the airflow becomes turbulent?

Answer 14

Because the chord line position changes.

Question 15

Unless otherwise stated in the poh, the actions to be taken to recover from a spin is:

Answer 15

1. close the throttle completely
2. keep the ailerons completely neutral.
3. apply full opposite rudder to the direction of the spin
4. move the control column forward to unstall the wings
5. when the spin stops, centralise the rudder
6. ease the aeroplane gently out of the dive.