Results of Supersonic Heat-Transfer Studies on Blunt Swept Leading Edges.
Abstract
Stagnation-line heat-transfer distributions were obtained on blunt swept leading edges at Mach 3.66 and a Reynolds number per foot of 210,000. Pressure distributions were obtained for comparable test conditions. The results illustrate the effects of various flow nonuniformities on leading-edge heat transfer and pressure, including those arising from finite span and nonuniform leading-edge sweep; free-stream nonuniformity induced by the bow shock of typical blunt body; boundary-layer interaction near the leading-edge root; and impingement of a trailing-tip vortex. None of these effects can be predicted analytically as yet, and all may lead to significant deviation from the levels based on infinite-cylinder theory. The importance of the individual results are discussed, and, where possible, appropriate design criteria are presented. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Mar 01, 1970
- Accession Number
- AD0869314
Entities
People
- Albert F. Gollnick Jr.
Organizations
- Massachusetts Institute of Technology