EXPERIMENTAL INVESTIGATION OF THE AERODYNAMIC CHARACTERISTICS OF 9 DEG HALF-ANGLE CONES WITH VARYING DEGREES OF BLUNTNESS AT MACH NUMBER 9
Abstract
A wind tunnel test was conducted in a 21 in. hypersonic facility to obtain force and moment data on right circular cones of varying degrees of bluntness. Normal forces, axial forces, and pitching moments were measured over an angle of attack range of -10 to +15 degrees, at Mach numbers of 7.25 and 9.00, and a Reynolds number range of 0.037 to 0.150 x 10 to the 6th power/in. Three 9-degree half-angle cones with ratios of nose tip radius to base radius of 0.03, 0.187, and 0.30 were tested. The experimental data was compared with theoretical data, and the two were in good agreement. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Apr 01, 1962
- Accession Number
- AD0275191