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12.6 Basic Aerodynamic Theory
12.6.2 Describe what an aerofoil is and distinguish between different aerofoil designs.
(a) leading edge;
(b) trailing edge;
(d) chord line;
- A straight line from the leading edge to the trailing edge.
- 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).
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:
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.
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