The simple linearized transonic flow theory as originally proposed by Oswatitsch and Keune [1] and by the present authors [2] is improved by considering and partially correcting its error. In this manner a theory which is easy to apply and which should be valid for a great number of smooth bodies is obtained. This improved theory predicts shock waves in the lower transonic regions. It is applied to a number of significant body and airfoil shapes and its predictions are compared with experiments and results of other theoretical investigations.

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