Tests in the Compressed Air Tunnel on thenAerofoils NACA OO15 and NACA OO3O With and Without Split Flap and on other Aerofoils of Various Thicknesses With a Split Flap

摘要

To obtain information on the effect of thickness on the aerodynamic characteristics of aerofoils with and without a split flap.nThe effect of rounding the ends of NACA 0030 was also examined. CL, CD and Cm were obtained over a range of Reynolds numbers with additional CD measurements at closer intervals of R on the two wings without flap. CDt 0 was also determined by the momentum method on NACA 0030.