本文主要探討極音速勢流微小擾動方程式 邊界值問題,並利用相似轉換法求出極音速流 經凸角扇形膨脹波流場之相似解及凹角楔形面 之壓縮波解,並計算出其斜震波之位置及其表 面壓力係數,經與完整斜震波理論所得之漸近 解比較,極音速勢流理論可獲得滿意之結果。 應用凹角及凸角之相似解,可解析地求出 極音速流經楔形翼剖面之流場解及翼前後緣斜 震波及曲線震波之位置及形狀。本文利用勢流 理論同時求出具攻角平板之升、阻力係數,其 與震波-膨脹波理論所得之結果比較,二者甚為 接近。 The similarity solutions of hypersonic small disturbance potential equation to the boundary value problem of centered expansion and compression waves are given. In particular, the analytical solutions of the wedge airfoil including oblique and curved shocks at leading and trailing edges are constructed. The lift and drag coefficients of flat plate with angle of attack are also calculated from potential theory and the result agrees well with that obtained from the shock-expansion theory.
關聯:
中國航空太空學會第三十四屆學術研討會論文集(一)=Proceedings of the AASRC 34th Aeronautics and Astronautics Conference ( I)，頁479-488
