Abstract
The application of linearized theory to the external aerodynamic design and analysis problem at supersonic speeds is discussed. Particular emphasis is placed on the use of a far field viewpoint since this concept makes it possible to treat thickness drag from a total system standpoint. For the lifting case, such an approach results in a decomposition of aircraft resistance into shock wave and vortex components. This decoupling allows an identification of the importance of such losses relative to one another and permits considerable latitude in modifications to reduce the drag in one mode without adversely interacting with the other. Representative comparisons of prediction with measurements are presented to illustrate the accuracy and limitations of the various procedures. Certain unresolved difficulties which arise in the application of potential theory to the aircraft design problem will be pointed out to identify areas requiring further development.
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