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| 題 名 | Numerical Study of the Viscous Transonic Flow around Hybrid Wing at High Angles of Attack=機翼及翼前緣翼於穿音速高攻角氣流計算研究 |
|---|---|
| 作 者 | 蘇盛竹; | 書刊名 | 中華技術學院學報 |
| 卷 期 | 29 2003.12[民92.12] |
| 頁 次 | 頁151-164 |
| 分類號 | 447.5532 |
| 關鍵詞 | 機翼; 高攻角氣流; Viscous flow; Hybrid wing; Surface flow patterns; Separation line; Vortex shedding; Shock vortex boundary interactions; |
| 語 文 | 英文(English) |
| 中文摘要 | 本文是以三維黏性流數值法計算機翼與翼前緣翼組合外型體飛行於穿音速高攻角之氣流特性研究。同時,本文數值方法可計算分析及檢視三維機翼表面複雜氣流形式、流體質點路徑、速度及壓力等特性。機翼表面上震波及高攻角渦游流所產生之分離流形式及強度與位置結果亦可正確地計算及分析。機翼上由翼前緣翼及翼前緣所產生的二渦旋流它們之間地相互干擾以及穿音速震波/渦懸流/邊界層之冒地相互干擾均可以精確計算模擬,並與風實驗結果作驗證比對。 |
| 英文摘要 | The object of this study is to develop a numerical method capable of solving the viscous flow around three-dimensional stake hybrid wing at high angle of attack. The ability of the numerical method to predict the complex flow characteristics of the surface flow patterns, off-surface flow visualizations, and surface pressure prediction are presented. The location of separation line and relative the strength and position of a vortex shed from a strake are present here. The interaction between the two primary vortices generated form the strake and leading edge are successfully simulated. Computed results demonstrated the effecting of the present method and show good agreement with experimental data. In addition, transonic shock/vortex/boundary interactions on the surface are discuses. |
本系統中英文摘要資訊取自各篇刊載內容。