The purpose of this experiment was to find the normal force and the lift curve slope by measuring the static pressure distribution around a symmetrical aerofoil.The experiment involved studying the distribution of pressure for different angles of attack

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Title

Pressure Distribution Around A Symmetrical Aerofoil

Introduction

The purpose of this experiment was to find the normal force and the lift curve slope by measuring the static pressure distribution around a symmetrical aerofoil.

The experiment involved studying the distribution of pressure for different angles of attack. There were five different angles of attack in the experiment - -4, 1,6,11 and 16 degrees.

To discuss about the experiment it is needed to understand some phrases. And they are as follows:

a) Aerofoil

b) Lift

c) Angle of Attack

d) Lift Coefficient

e) Drag

f) Stagnation point

Aerofoil

An aerofoil or airfoil section is a two-dimensional object, the shape of the cross-section of the wing, with the function of producing a controllable aerodynamic force by its motion through the atmosphere. To be useful this aerodynamic force must have a lifting component which is much greater than the drag component. In a powered aircraft the motion through the air is provided by the thrust so, in effect, the aerofoil is a device that converts thrust into lift.

Normally the aerofoil is incorporated into a wing with