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) : Marshall,John A. ; Srinivasan,S.
Report Date : JUN 1971
Pagination or Media Count : 74
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)
Descriptors : (*NOSE CONES, COOLING), (*HEAT SHIELDS, ABLATION), (*REENTRY VEHICLES, HEAT SHIELDS), CARBON, PHENOLIC PLASTICS, FLIGHT TESTING, MODEL TESTS, TUNGSTEN, STAINLESS STEEL, THERMODYNAMICS, HELIUM, CONICAL BODIES
Subject Categories : Guided Missile Reentry Vehicles
Distribution Statement : APPROVED FOR PUBLIC RELEASE