The Downstream Effects of Transpiration Cooling on the Heat Shield of a Slender Nose Cone.
Technical rept. Feb 69-Dec 70,
AIR FORCE MATERIALS LAB WRIGHT-PATTERSON AFB OHIO
Pagination or Media Count:
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 Btulb, and to velocities up to Mach 10. It was demonstrated that a helium coolant flow rate of about .00036 lbsec 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
- Guided Missile Reentry Vehicles