Experimental Study of Hypersonic Wing/Fin Root Heating at Mach 8
Abstract
A series of tests were conducted at both "low" and "high" pressure conditions, representing atmospheric conditions at Mach 8 and a "high heating" case respectively. Results exhibited good correlation in peak heating showing higher heating loads for both increases in pressure and decreases in sweep angle. While conclusions about flow topology remain to be made, an unexpected observation is that the shock impingement, or peak heating, occurred farther from the wing root when moving from a low to high pressure condition. Additionally the effect of the conditions on peak heating on the wing appeared to decrease with increasing sweep angle with the relative peak heating for a high pressure shot at 700%, 200% and 60% for 45 deg, 55 deg and 65 deg of sweep respectively.
Document Details
- Document Type
- Technical Report
- Publication Date
- Dec 27, 2012
- Accession Number
- ADA572021
Entities
People
- Michael K. Smart
Organizations
- University of Queensland