点击下载:《热力学》课程教学资源(PPT课件)Chapter 11 SUBSONIC COMPRESSIBLE FLOW OVER AIRFOILS:LINEAR THEORY(2/2)
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B2=(1-M2) 209+0=0 or X n= By 0(,)=B0(x,y)0 ˆ ˆ 2 2 2 2 2 = + x y (1 ) 2 2 = − M = x = y ( , ) ˆ ( ,) = x y
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点击下载:《热力学》课程教学资源(PPT课件)Chapter 11 SUBSONIC COMPRESSIBLE FLOW OVER AIRFOILS:LINEAR THEORY(2/2)
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