Analysis of wings using Airfoil NACA 4412 at different angle of attack
نویسندگان
چکیده
The purpose of this paper is to analysis the basic aerodynamic theory of wings and the provide an introduction to wind tunnel testing. This is followed by the result from the wind tunnel testing of a NACA4412 and the analysis of the data. Lift increase at the angle of attack increase at certain point and at this point it become maximum. After that if the angle of attack is increased by further, drag become the dominant factor and the wind enters the stall mode.
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