Local Pressure Distribution On A Blunt Delta Wing For Angles Of Attack Up To 35 Degrees At Mach Numbers Of 34 And 47 PDF Download

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).