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WIND TUNNEL EXPERIMENTAL PROCEDURE
Jan 10, 2014 · A = N'*.0608+A'*.5912 P= -N'*.1336+A'*.0119+P'*1.182 Using the corrected values of axial force A and normal force N the lift and drag can be calculated from the relations: Lift = N cos α - A sin α Drag = A cos α + N sin α For conversion to lift, drag, and pitching moment coefficients the wing has a span width b=
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