Tests in the compressed air tunnel on the aerofoils NACA 0015 and NACA 0030 with and without split flap and on other aerofoils of various thicknesses with a split flap

Abstract

To obtain information on the effect of thickness on the aerodynamic characteristics of aerofoils with and without a split flap. The following 4 ft. by 8 in. rectangular aerofoils were tested :- NACA 0015 and NACA 0030 with and without a split flap 0.lc wide at 90 deg. to wing surface and at 0.lc from trailing edge. NACA 0012, NACA 23012, RAF 28 and RAF 48 with flap. The effect of rounding the edge of the flap was considered on NACA 0015. A comparison made with a 0.2c flap at 50 deg. to wing surface and at 0.2c from trailing edge on NACA 0015 and RAF 48. The effect of rounding the ends of NACA 0030 was also examined. C L, C D and C M were obtained over a range of Reynolds numbers with additional C D measurements at closer intervals of R on the two wings without flap. C D,0 was also determined by the momentnm method on NACA 0030.