A 14.25-percent-thick, natural-laminar-flow airfoil, the S406, for rotorcraft applications has been designed and analyzed theoretically and verified experimentally in The Pennsylvania State University Low-Speed, Low- Turbulence Wind Tunnel. The two primary objectives of high maximum lift and low profile drag have been achieved. The constraint on the airfoil thickness has been satisfied, but the one on the pitching moment has not. The airfoil exhibits a docile stall. Comparisons of the theoretical and experimental results generally show good agreement.
Design and Experimental Results for the S406 Airfoil
2010
69 pages
Report
Keine Angabe
Englisch
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