Abstract:

This experimental investigation of the flow field over NACA 0014 aerofoil is done under the influence of different velocity of air and angle of attack. A low speed open type wind tunnel was used to perform the investigation. Main objective is to perform this investigation is to determine the aerodynamic (lift and drag) force coefficient of the aerofoil under two different Reynolds number 2.2×10⁵ and 2.7×10⁵. Attack angle was varied from 0^o to 18^o. Maximum lift coefficient was obtained at 15^o attack angle.

Keywords: Aerofoil, angle of attack, pressure coefficient, Reynolds number, lifts and drag coefficient.

Nishant Singh Kushwah

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