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Inverse design method for wings of supersonic transport
Description
A practical inverse design method for supersonic airfoils/wings has been developed. The method is based on Takanashi's iterative "residual-correction" concept. A geometry that materializes a specified pressure distribution is sought by solving an integrodifferential form of the linearized small perturbation (LSP) equation. The integration is limited to the Mach forecone from the point of interest. Several design results are presented Nomenclature
Journal
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- 36th AIAA Aerospace Sciences Meeting and Exhibit
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36th AIAA Aerospace Sciences Meeting and Exhibit 1998-01-12
American Institute of Aeronautics and Astronautics (AIAA)