Abstract
A computer program is developed to optimize the shape of a nacelle installed in a supersonic aircraft for minimum drag. The program is also capable of optimizing the wing camber of the same aircraft. As a unique feature, the present code accounts for the aerodynamic forces on the entire airplane in contrast to previous wing camber optimization codes that included only the wing forces. The program is based on a panel-method analysis code by Woodward, and the accuracy of the program is checked with the available wind-tunnel data on isolated components as well as full configurations. The computed results are in general agreement with the available data. The results of several optimization test runs are presented and show agreement with trends predicted by other researchers based on theoretical and experimental studies. At higher angles of attack, when supersonic vortex lift becomes significant, the analysis code underpredicts the aircraft lift coefficient.
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