A 14.22-percent-thick, slotted, natural-laminar-flow (SNLF) airfoil, the S414, 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 constraint on the airfoil thickness has been satisfied. The airfoil exhibits an abrupt stall. Comparisons of the theoretical and experimental results show good agreement overall. Comparisons with the S406 and S411 airfoils, which have similar design specifications, confirm the achievement of the objectives.
Design and Experimental Results for the S414 Airfoil
2010
97 pages
Report
Keine Angabe
Englisch
Design and Experimental Results for the S415 Airfoil
NTIS | 2010
|Design and Experimental Results for the S406 Airfoil
NTIS | 2010
|Design and Experimental Results for the S407 Airfoil
NTIS | 2010
|Design and Experimental Results for the S411 Airfoil
NTIS | 2010
|