Pressure Distributions at M

Abstract

Results are presented for wind tunnel tests at M(infinity) = 3.51 on four wings with pointed vertices and sharp leadlng edges. Two conical models were tested through a wide range of angles of incidence and yaw and the results clearly demonstrate the stabilising effect of dihedral. Two simple non-conical wings were also tested and it 1s shown, in this case, that the pressure on the compression surfaces may be approximately deduced from an 'equivalent' conical wing.