The development of airfoil configurations to provide shock-free flow at supersonic speeds is discussed. The airfoil design creates local supersonic regions on the surfaces of the apansion waves reflected at sonic lines come back to the airfoil surface as compression waves which decelerate the local supersonic flow isentropically to subsonic speeds. A characteristic of the airfoil section is that a negative pressure peak exists close to the leading edge. Schlieren photographs of the shock wave patterns on typical airfoil sections are provided. Graphs of the pressure distribution for various airfoil configurations and conditions of flight are included.
On Peaky Airfoil Sections
1973
43 pages
Report
Keine Angabe
Englisch
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