The Downstream Effects of Transpiration Cooling on the Heat Shield of a Slender Nose Cone.
Abstract
An experimental investigation was performed to determine the effects of steady state upstream transpiration cooling on the surface temperature of a carbon phenolic downstream heat shield of an eight-degree half-angle cone. The test model was exposed to gas stream stagnation temperatures of 5950R to 8460R, enthalpies up to 4340 Btu/lb, and to velocities up to Mach 10. It was demonstrated that a helium coolant flow rate of about .00036 lb/sec was sufficient to prevent model decomposition (charring) or ablation over a 100 second period. The heat losses from the temperature sensing devices (calorimeters) were estimated to be of the order of six to seven percent. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Jun 01, 1971
- Accession Number
- AD0731757
Entities
People
- John A. Marshall
- S. Srinivasan
Organizations
- Air Force Research Laboratory