Publication: Experimental and computational aerodynamic studies of aerofoils
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Date
2002-03-01
Authors
Mohamed, Rahimah
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Abstract
Aerodynamics parameters of an aerofoil can be determine by doing the wind tunnel test.
In this project, wind tunnel test has been done on NACA 4412, NACA 23012, wing and
canard of Eagle aircraft in a subsonic wind tunnel in School of Mechanical Engineering.
For NACA 4412, wing and canard, the experiment is done to determine the value of
coefficient of lift and drag. Experiment is done with velocity range from 27 m/s to 38 m/s
and angle of attack ranging from 0° to 16°. For NACA 23012, experiment done to
determine the pressure distribution around an aerofoil. The experiment carried out at
speed of 26 m/s, angle of attack 0° and Reynolds number 1.67 x 10-5. The wind tunnel
test show the relation between angle of attack with the lift and drag coefficient and also
give the pressure distribution. Simulation using FLUENT 5.5 shows clearly the flow over
an aerofoil. This result has give clear contour of pressure and velocity distribution over
the surface of aerofoil.