This report deals with experimental investigations on four thin airfoils (d/1 = 0.05 - see list of symbols), three supercritical airfoils being compared with a conventional one with reference to aerodynamic efficiency. The investigations, conducted in the DFVLR's Brunswick transonic wind tunnel, at Mach numbers ranging from 0.6 to 0.95 and at a Reynolds number 4.10 to the 6th power (6.10 to the 6th power) show the superiority of supercritical airfoil design. This is demonstrated in terms of overall coefficients, efficiency limits and, in particular cases, pressure distributions.
Wind Tunnel Investigations on Thin Supercritical Airfoils in the High Subsonic Flow Regime
1983
65 pages
Report
Keine Angabe
Englisch
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