An experimental investigation was conducted to measure the pressures on two 60 degree swept delta wings with cylindrical leading edges of 0.25-inch radii and dihedral angles of 0 and 45 degrees. The tests were conducted at a Mach number of 4.95 and a stagnation temperature of 400 F. The test-section unit Reynolds number was 15.19 x 10 to the 6th power and the angle of attack was varied from 0 to 20 degrees. The results of the investigation indicated that, in general, Newtonian theory would not predict the pressure distri ution on the model in a plane normal to the leading edge for angles of attac greater than zero. A method which utilizes a linear combination of viscous and inviscid pressure terms, developed by Creager for predicting pressures on blunt-leading-e ge delta wing at angles of attac, was in good agreement with the measured pressure distributions. The stagnationline pressure level could be predicted within!9 percent by using the ideal-gas normal-shock relationship with the normal component of the free-stream Mach number. (Author).