A 14.12-percent-thick, natural-laminar-flow airfoil, the S415, intended for the rotor of a helicopter in hover 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 pitching moment has been satisfied. The airfoil exhibits a docile stall. Comparisons of the theoretical and experimental results generally show good agreement.
Design and Experimental Results for the S415 Airfoil
2010
60 pages
Report
Keine Angabe
Englisch
Aerodynamics , Aerodynamic characteristics , Airfoils , Moments , Low velocity , Profiles , Low drag , Low level , High lift , Wind tunnels , Hovering , Turbulence , Pitch(Motion) , Helicopters
Design and Experimental Results for the S411 Airfoil
NTIS | 2010
|Design and Experimental Results for the S407 Airfoil
NTIS | 2010
|Design and Experimental Results for the S414 Airfoil
NTIS | 2010
|Design and Experimental Results for the S406 Airfoil
NTIS | 2010
|