Four thin airfoils (t/c = 0.05) were investigated experimentally. The aerodynamic efficiency of three supercritical airfoils is compared with that of a conventional one. The investigation was conducted in a transonic wind tunnel within a Mach number range of 0.6 to 0.95 and at Reynolds numbers 4 million to 6 million. Results show the superiority of supercritical airfoil design. This is explained, referring to overall aerodynamic coefficients, limits of efficiency, and in special cases to pressure distributions.
Wind Tunnel Investigations on Thin Supercritical Airfoils in High Subsonic Flow
1982
63 pages
Report
Keine Angabe
Englisch
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