NACA-TN-1759

Abstract

A high-speed wind-tunnel investigation of a taporod wing of NACA 66-series airfoil sections equipped with split flaps has been conducted at Mach numbers up to 0.585 to determine the effects of compressibility on the normal-force, pressure, and load characteristics. Both 55-percent-span and 98-percent-span flaps deflected 60&#176; and having chords of 20 percent of the wing chord were tested. The range of angle of attack investigated was from approximately -4&#176; up through the stall. <br>The maximum normal-force curves for the wign with flaps were some-what similar in shape to the maximum lift curve for the wing without flaps, although Mach number effects became apparent at lower speeds and were larger for the wing with flaps. The maximum normal-force coefficient for the wing with partial-span split flaps reached a minimum value of 1.53 at a Mach number of 0.295 and a maximum value of 1.79 at a Mach number of 0.585. The maximum normal-forces coefficient for the wing with full-span split flaps reached a minimum value of 1.87 at a Mach number of 0.300 and a miximum value of 2.22 at a Mach number of 0.55⁰. There is further evidence that the rapid rise in maximum lift coefficient at higher Mach numbers is due to the sharp leading edge of the wing as comber, camber location, and trailing-edge angle appear to have little or no effect on the rise