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

蘇盛竹(Shen-Jwu Su)

《中華技術學院學報》 29期 (2003/12) Pp. 151-164

https://doi.org/10.7095/JCIT.200312.0151

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体飛行於穿音
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、流体質點路徑、速度及壓力等特性。機翼表面上震波及高攻角渦
漩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/
邊界層之間地相互干擾均可以精確計算模擬，並與風洞實驗結果作驗證比對。

並列摘要

The object of this study is to develop a numerical method capable of solving theviscous flow around three-dimensional stake hybrid wing at high angle of attack. Theability of the numerical method to predict the complex flow characteristics of thesurface flow patterns, off-surface flow visualizations, and surface pressure predictionare presented. The location of separation line and relative the strength and position of avortex shed from a strake are present here. The interaction between the two primaryvortices generated form the strake and leading edge are successfully simulated.Computed results demonstrated the effecting of the present method and show goodagreement with experimental data. In addition, transonic shock/vortex/boundaryinteractions on the surface are discuses.

並列關鍵字

viscous flow ； hybrid wing ； surface flow patterns ； separation line ； vortex shedding ； shock/vortex/boundary interactions