Consider a rectangular wing mounted in a low - speed subsonic wind tunnel. The wing model completely
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Consider a rectangular wing mounted in a lowspeed subsonic wind tunnel. The wing model
completely spans the test section so that the flow sees essentially an infinite wing. If the wing has an
NACA aerofoil section and a chord of m a calculate the lift, drag per unit span and the lift
to drag ratio when the airflow pressure, temperature, velocity and viscosity are l atm, K ms
and times respectively. The angle of attack is deg Cl Cd
calculate the net skinfriction drag coefficient, the total skinfriction drag, and the total pressure drag
force on the wing
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