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.
|出版ステータス||Published - 1998|
|イベント||36th AIAA Aerospace Sciences Meeting and Exhibit, 1998 - Reno, United States|
継続期間: 1998 1 12 → 1998 1 15
|Other||36th AIAA Aerospace Sciences Meeting and Exhibit, 1998|
|Period||98/1/12 → 98/1/15|
ASJC Scopus subject areas