A higher-order panel method has been developed for the analysis of linearized subsonic and supersonic flow over configurations of general shape. This method overcomes many of the slender body limitations of present day programs in the analysis of supersonic configurations. The capabilities of this method are demonstrated through its application to the analysis of realistic supersonic cruise configurations. Comparisons are shown with experimental data and with results from other methods in current use. These comparisons demonstrate the unique capabilities of a major new software system called PAN AIR soon to be available as a general boundary value problem solver.
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