WING-BODY INTERACTIONS AT A MACH NUMBER OF 9.5.
Abstract
Several delta wing-body configurations were tested at a Mach number of 9.5 to determine the effects of the radius of curvature of the wing-body junction on the spanwise pressure and aerodynamic heating distributions. The results indicate that although the pressure levels longitudinally may change there is essentially no pressure variation along the span resulting from the change in said radius of curvature; however, there is considerably spanwise variation in the values of aerodynamic heating. These variations in general, agree with the theoretical predictions of hypersonic flow in a corner alined with the free-stream velocity. Finally, heating distribution and oil flow visualization pictures confirm the theoretically predicted vortical flow in the region of the wing-body juncture. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Sep 01, 1967
- Accession Number
- AD0831249
Entities
People
- Bertram K. Ellis
- David W Taylor
- Roger J. Furey