Abstract
IN THE EXISTING SOLUTIONS of the thin airfoil problem, the determination of the steady state lift and moment of an airfoil of small camber and thickness, as given by Birnbaum, von Karman, C. B. Millikan, etc., 4> 5 the velocity potential for the flow is determined, and the lift distribution and the integrated lift and moment are found from this result. It appears that a somewhat simpler solution of this problem can be obtained by working directly with the velocity components rather than with the velocity potential. This same method can also be used to advantage in many threedimensional wing problems. An important feature of this method is that the inverse problem, the determination of an airfoil shape that will produce a given lift distribution, can be solved just as easily as the direct problem. Both the direct and the inverse problem will be investigated by this method in the present paper. The notations used in the analysis are as follows:
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