Chapter 6

Question 1

CLMAX

Answer 1

Stalling angle of attack (or critical angle of attack).
Abbreviated to stalling angle or critical angle.
The greatest value that the coefficient of lift can achieve. It occurs at the critical (or stalling)

Question 2

Critical angle of attack

Answer 2

Is the point of CLMAX. Also known as the stalling angle of attack. The highest alpha at which the aerofoil does not stall.

Question 3

Lift coefficient (CL)

Answer 3

A dimensionless number which describes how effective the aerofoil is at producing lift for a given airflow speed and surface area. Gives the amount of lift produced per unit area and unit dynamic pressure.

Question 4

What are the three main factors effecting CL in low subsonic flight?

Answer 4

Angle of attack
Thickness
Camber of the aerofoil

Question 5

What is A(CRIT) and CL(MAX)?

Answer 5

This is the highest Alpha in which the aerofoil does not stall. It is NOT the alpha at which the aerofoil stalls!!

Question 6

What is the lift equation?

Answer 6

L = 1/2 P v(2) s CL