12.6 Basic Aerodynamic Theory

12.6.2 Describe what an aerofoil is and distinguish between different aerofoil designs.

12.6.4 Define:

(a) leading edge;

(b) trailing edge;

(c) chord;

(d) chord line;

• A straight line from the leading edge to the trailing edge.

(e) thickness;

(f) camber.

• Distance between chord line and camber line. 
• The greater the distance the greater the camber. 
• Camber is a direct measure of an aerofoils coefficient of lift (CL).
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12.6.6 Define relative airflow and angle of attack.

12.6.8 Explain Bernoulli’s Theorem in simple terms.

In a stremlined flow of an ideal fluid the sum of all energies will remain a constant.

12.6.10 Describe streamline airflow around an aerofoil.

12.6.12 Explain the changes which occur to dynamic and static pressure wherever the speed of the airflow is:

(a) increased;

(b) decreased.

12.6.14 With the aid of diagrams, explain:

(a) venturi effect;

(b) the pressure distribution around an aerofoil which is producing lift.

12.6.16 Define the terms:

(a) total reaction (TR);

(b) centre of pressure (CP).

12.6.18 Describe how TR and CP change with increasing angle of attack for a lifting aerofoil.

12.6.20 Show how movement of the CP varies between symmetrical and non-symmetrical aerofoils.