本文主要探討穿音速微小擾動方程式邊 界值問題,並利用相似轉換法,求出穿音速(微 超音速M/sub .inf./.gtoreq.2)流經凸角之扇 形膨脹波流場及凹角楔形面之壓縮波流場相似 解,並計算出其斜震波之位置與表面壓力係數, 經與完整斜震關係式所得之精確解比較,而獲 得滿意之結果。 應用凹角及凸角之相似解,可解析地求 出穿音速流經雙楔形翼剖面邊界值問題之流場 解,及翼前、翼後緣震波之形狀、位置、及各 項氣動力係數,以提供數值計算之參考。 The similarity solution to the boundary value problem of transonic centered expansion and compression waves is given. In particular, its application to finding the analytical solution of the double wedge airfoil with leading and trailing shock is exhibited. The similarity solution is used to check the accuracy in the numerical results.
Relation:
中國航空太空學會民國八十年學術研討會論文集=Proceedings of the 1991 Aeronautics and Astronautics Conference of the Aeronautical and Astronautical Society of the R.O.C.，頁51-62
