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.
|Publication status||Published - 1998 Jan 1|
|Event||36th AIAA Aerospace Sciences Meeting and Exhibit, 1998 - Reno, United States|
Duration: 1998 Jan 12 → 1998 Jan 15
|Other||36th AIAA Aerospace Sciences Meeting and Exhibit, 1998|
|Period||98/1/12 → 98/1/15|
ASJC Scopus subject areas
- Space and Planetary Science