A 14-percent-thick airfoil, the S411, intended for rotorcraft applications has been designed and analyzed theoretically and verified experimentally in The Pennsylvania State University Low-Speed, Low-Turbulence Wind Tunnel. The airfoil incorporates a 5-percent-chord tab. The two primary objectives of high maximum lift and low profile drag have been achieved. The constraint on the pitching moment has been exceeded; that on the airfoil thickness, satisfied. The airfoil exhibits a docile stall. Comparisons of the theoretical and experimental results generally show good agreement. Comparisons with the S406 airfoil confirm the achievement of the objectives.
Design and Experimental Results for the S411 Airfoil
2010
76 pages
Report
No indication
English
NTIS | 2010
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