超音速與極音速凹角壓縮流場漸近解之統合

淡江大學機構典藏 > 工學院 > 航空太空工程學系暨研究所 > 會議論文 > Item 987654321/38359

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题名:	超音速與極音速凹角壓縮流場漸近解之統合
其它题名:	A Unified Approach for Supersonic and Hypersonic Flow Past a Corner
作者:	馮朝剛
贡献者:	淡江大學航空太空工程學系
关键词:	超音速尖角非線性理論;變形座標法;相似法;極音速全場小擾動理論;Supersonic nonlinear theory;hypersonic nonlinear theory;similarity solution;corner flow;oblique shock wave
日期:	2006-03
上传时间:	2010-01-11 15:08:41 (UTC+8)
出版者:	臺北縣淡水鎮：淡江大學
摘要:	"本文利用漸近展開法建構超音速與極音速凹角壓縮流動邊界值問題，並利用相似法求出其流場解及陡變條件以求出其震波位置，經與斜震波理論所得之結果比較而驗證出本文結果之正確性。同時將超音速凹角壓縮流動邊界值問題轉換至極音速流場，其所求得之結果與直接由極音速全場邊界值問題所求得之結果完全相同，換言之，超音速凹角壓縮流動全場解統合了極音速全場解。" "Due to the singularity at the corner, a supersonic or hypersonic flow past a corner is essentially a nonlinear problem. The governing equations for these flows are supersonic and hypersonic nonl inear small disturbance potential equations. The similarity solutions of these boundary value problems are derived in this work and the results agree well with the asymptotic solution from the oblique shock wave theory. The governing equations for the supersonic and hypersonic flows are completely different. It is worth mentioning that the asymptotic solution of hypersonic flow past a corner can be approached by the asymptotic solution of supersonic flow using the expansion of free Mach number in terms of hypersonic simi lari ty parameters. The results of this study show that the supersonic nonlinear solution constructed for the corner flow is correct and the solutions for corner floware unified for supersonic and hypersonic small disturbance theories."
關聯:	第五屆海峽兩岸航空太空學術研討會論文集，頁13-22
显示于类别:	[航空太空工程學系暨研究所] 會議論文

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