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首頁> 美國政府科技報告 >Theoretical and Experimental Investigations of Jet Parallel to Wing in Cross Flow. Part I. Numerical Integration of Three-Dimensional Flow. Part II. Experimental-Laser Velocimeter Flow Field Investigations.
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Theoretical and Experimental Investigations of Jet Parallel to Wing in Cross Flow. Part I. Numerical Integration of Three-Dimensional Flow. Part II. Experimental-Laser Velocimeter Flow Field Investigations.

機譯：橫流中平行于機翼的射流理論與實驗研究。第一部分：三維流動的數(shù)值積分。第二部分。實驗 - 激光測速儀流場調(diào)查。

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Theoretical and experimental analysis of jet flow parallel to a wing and in cross flow is presented. A numerical model is developed to integrate the three-dimensional flow field equations. A parabolic approximation is assumed and marginally stable solutions are obtained. It is concluded that stability problems arise because of a combination of an incomplete theoretical model and an inadequate numerical integration scheme. Turbulence parameters are obtained from laser velocimeter measurement of the flow field. Laser and surface pressure tests were conducted. Pressure tests include low and high angle of attack results of spanwise blowing over a low aspect ratio semi-span model. High angle of attack data include the effects of leading edge vortex control by spanwise blowing. Only low angle of attack data are presented for the laser flow field tests.

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