Effect of nose shape and trailing-edge bluntness on the aerodynamic characteristics of an unswept wing of aspect ratio 3.1, taper ratio 0.4, and 3-percent thickness

The effects of blunting the trailing edge and/or rounding the leading edge upon the lift, drag, and pitching-moment characteristics of a plane tapered wing in combination with a body have been experimen~ly investigated at Mach numbers ranging from 0.61 to 0.93 and from 1.20 to 1.$)0.Results indicate that blunting the trailing edge to 0.3 of the maximum airfoil thickness reduced the forward movement of the aerodynamic center, noted for the sharp-trailing-edge sections at high subsonic speeds without, in.general, a significant reduction in the maximum liftdrag ratio.At all Mach numbers, blunting the trailing edge increased the minimum drag.Rounding the leading edges of the wings having either the sharp or the blunt trailing edges decreased the minimum drag andj tith one exception, increased the maximum lift-drag ratios at subsonic speeds.At supersonic speeds the opposite effects were noted.