Heat-Transfer Tests on a Full and 1/4 Scale AIM-9E Sidewinder Missile and a 1/15 Scale GBU-8 Guided Bomb Unit at Mach Numbers of 1.5, 2.0 and 2.5
Abstract
Heat transfer tests were conducted in the Arnold Engineering Development Center (AEDC) Supersonic Wind Tunnel A on a 1/4 and full scale AIM- 9E Sidewinder Missile and a 1/15 scale GBU-8 Guided Bomb Unit. The purpose of the tests was to obtain heating distributions on the stores for wind tunnel/ flight correlation and as baseline data for input to an analytic thermal response code. Heat transfer coefficient, adiabatic wall temperature, and Schlieren/shadowgraph photographic data were obtained. Tests were conducted at Mach numbers 1.5, 2.0 and 2.5 and free-stream unit Reynolds numbers of 1 x 10 to the 6th power to 5 x 10 to the 6th power. Model angle of attack was varied over the range from -2 to 4 degrees. In addition, performance evaluation tests were conducted on a stand-alone flight data system designed to gather flight test heat-transfer data.
Document Details
- Document Type
- Technical Report
- Publication Date
- Oct 01, 1979
- Accession Number
- ADA091805
Entities
People
- W. K. Crain
Organizations
- Arnold Engineering Development Complex