極音速膨漲與壓縮流動邊界值相似解及其應用

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Title:	極音速膨漲與壓縮流動邊界值相似解及其應用
Other Titles:	The similarity solutions of the boundary value problem of hypersonic expansion and compression flow with application
Authors:	馮朝剛;高百齡
Contributors:	淡江大學航空太空工程學系
Keywords:	極音速流;相似解;膨脹波;壓縮波;機翼;斜入震波;攻角;阻力係數;Hypersonic Flow;Similarity Solution;Expansion Wave;Compression Wave;Wing;Oblique Shock;Angle Of Attack;Drag Coefficient
Date:	1992-11
Issue Date:	2010-01-11 15:10:21 (UTC+8)
Publisher:	成功大學
Abstract:	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.
Relation:	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
Appears in Collections:	[Graduate Institute & Department of Aerospace Engineering] Proceeding

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