Accession Number:

AD0731757

Title:

The Downstream Effects of Transpiration Cooling on the Heat Shield of a Slender Nose Cone.

Descriptive Note:

Technical rept. Feb 69-Dec 70,

Corporate Author:

AIR FORCE MATERIALS LAB WRIGHT-PATTERSON AFB OHIO

Personal Author(s):

Report Date:

1971-06-01

Pagination or Media Count:

74.0

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 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

Subject Categories:

  • Guided Missile Reentry Vehicles
  • Thermodynamics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE