WIND TUNNEL TESTS OF THERMAL INSULATION PROTECTION SYSTEMS FOR MACH NUMBER 3.0 TO 4.4 FLIGHT VEHICLES
Abstract
Particular considerations of importance in the insulating systems were the rates of heat transfer to the aluminum skin and the frictional and thermal effects on the insulating materials themselves. The systems were tested over an angle-of-attack range of -3 to + 7 degrees and flight conditions that simulated rates of heat transfer, skin friction and insulated wall temperatures for altitudes of 60,000 to 80,000 feet and corresponding Mach numbers of 3.0 to 4.4. Stagnation temperatures ranged from 570 to 890 F at a stagnation pressure of 2.8 atmospheres and a free stream Mach number of 2.5. These flow conditions produced equilibrium wall temperatures on the model of 500 to 800 F, which corresponds to the free flight skin temperatures that would result due to the balance between aerodynamic heating and the heat loss from the skin by ra iation, for the simulated flight conditions. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Nov 15, 1961
- Accession Number
- AD0270704
Entities
People
- Lowell Smith
Organizations
- General Dynamics