HEAT TRANSFER AND PRESSURE ON A SLENDER CYLINDER IN VISCOUS HYPERSONIC FLOW.
Abstract
Wall heat transfer and pressure were measured on a long, slender, cone-cylinder at positions far enough aft that transverse curvature effects were large. The tests were performed in the shock tunnel at M = 20 at Reynolds numbers of 0.8 to 4.0 x 10 to the 5th power based on free stream conditions and distance from the nose. The measurements were compared with hypersonic viscous interaction predictions. The resulting correlations showed that the strong interaction solution of the viscous interaction theory appeared to give accurate estimates of the heat transfer for large transverse curvature, regardless of shock strength. However, the pressures measured on the body were quite low, indicating a weak shock on the body. Hence, the present theory does not apply. Future pressure predictions will require consideration of finite shock strengths. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Apr 30, 1969
- Accession Number
- AD0690165
Entities
People
- Robert L. Varwig
Organizations
- The Aerospace Corporation