An 11.43-percent-thick airfoil, the S407, 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 two primary objectives of high maximum lift and low profile drag have been achieved. The constraints on the pitching moment and the airfoil thickness have been satisfied. The airfoil exhibits a sharp stall, which does not meet the design objective. Comparisons of the theoretical and experimental results generally show good agreement.
Design and Experimental Results for the S407 Airfoil
2010
88 pages
Report
Keine Angabe
Englisch
Aerodynamics , Fluid Mechanics , High lift , Low drag , Airfoils , Low velocity , Stalling , Wind tunnel tests , Low level , Laminar flow , Reynolds number , Rotary wing aircraft , Moments , Turbulence , Pitch(Motion) , Profiles , Sbir(Small business innovation research) , Sbir reports , Sbir topic a06-006 phase 2 , Rotorcraft
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