Abstract
Arbitrary deformations which include the special cases of wing camber and twist provide unique problems to the analyst when localized loadings are to be determined. Other than twist and camber, deformations in the lifting surfaces may occur from high loadings due to severe maneuverability requirements or from aerodynamic heating or combinations thereof. Existing supersonic potential flow theories appear to be inadequate in predicting pressures under these conditions and numerical finite-difference methods have excessive computer requirements if the whole three-dimensional wing is modeled. In the present work a new method is presented which retains the simplicity of three-dimensi onal potential flow theories yet incorporates desirable features of finite-element techniques. The method utilizes planar three-dimensional finite wing theory overlaid with vorticity paneling to account for perturbations due to the deformations. The solution is stable (nonoscillatory) and requires minimal computer time and storage. Results for three deformed mean lines for two separate planform geometries are presented with excellent agreement with experimental data.
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