Calculation of flow angle immediately behind trailing edge of flat plate airfoil and airfoil with thickness, on basis of oblique shock and Prandtl-Meyer wave theory; deflection angle of flat plate airfoil at given Mach Number is shown to first order to vary as fourth power of angle of attack; mechanism of return of flow downstream of airfoil to free stream direction.
Flow at rear of two-dimensional supersonic airfoil
J Aeronautical Sciences
Journal of the Aeronautical Sciences ; 15 , n 3 ; p 167-170
1948
4 pages
Article (Journal)
English
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Flow at the Rear of a Two-Dimensional Supersonic Airfoil
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