Investigates the pressure distribution around an aerofoil. It includes a NACA0020 symmetrical aerofoil mounted in a duct with transparent sides. The duct fits onto the contraction of the Air Flow Bench.

The aerofoil has pressure tapings on its upper and lower surfaces, six on each surface. These tapings connect to an integral manifold, for connection to a suitable manometer (not include). Students find the pressure distribution around the aerofoil and calculate the lift force. The angle of incidence of the aerofoil is adjustable and shown by a protractor scale.

EXPERIMENTS INCLUDE:

• Pressure distribution around an aerofoil
• Lift characteristics and stall angle of an aerofoil