Study is made to provide design information which would aid in prediction of turbulent separation for aerodynamic devices, such as compressor blades, flaps, spoilers, and diffusers; results show that Mach and Reynolds number, and model shape all are important variables.
Experimental investigation of pressure rise required for incipient separation of turbulent boundary layers in two-dimensional supersonic flow
NASA -- Memo
National Aeronautics and Space Administration -- Memorandums ; Memo 1-21-59A
1959
48 pages
Report
Englisch
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