It is almost thirty years since the method of complex characteristics led to the design of shocklesa airfoils that looked like practical wing sections [1,10]. At about the same time Murraan and Cole invented their simple, efficient upwind difference scheme to calculate transonic flows [9]. Soon computational fluid dynamics became the favorite tool of supercritical wing technology [2]. However, it was Murman's analysis concept that really worked, while only a few specialists were able to extract from the design method examples as successful as the Korn airfoil.
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