Compact Transpiration Cooling Free-Jet Test Results and Comparison with Theory.

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Abstract:

A series of free-jet tests has been carried out to obtain experimental data for use in evaluating the accuracy of a Compact Transpiration Cooling computer program. Nominal test conditions were Mach 2, 115 psia total pressure, and 500F total temperature. The test model was a flat plate with partially semicylinder leading edge nitrogen gas was used as the transpirant. Tests were carried out for a wide range of coolant flow rates and the results correlated with theory. Good agreement was obtained between measured and computed results of plenum pressure variation, porous surface temperatures without transpiration cooling, and solid surface temperatures for all runs. However, the predicted temperatures for the stagnation line on the porous matrix surface were consistently lower than the measured values. Author

Author(s):
Newman, Robb W.
Author Organization(s):
JOHNS HOPKINS UNIV SILVER SPRING MD APPLIED PHYSICS LAB
Descriptive Note:
Technical memo.,
Pagination:
0078

Security Markings

DOCUMENT & CONTEXTUAL SUMMARY

Distribution:
Approved For Public Release

RECORD

Collection: TR
Identifying Numbers
Report Number(s):
APL-TG-1178
Contract/Grant Number(s):
N00017-72-C-4401
 Subject Terms
Communities of Interest:
No COI(s) Identified
Descriptor(s):
(*AERODYNAMIC HEATING, *FILM COOLING), LEADING EDGES, COOLANTS, BOUNDARY LAYER, SUPERSONIC NOZZLES, ORIFICES, FLAT PLATE MODELS, HEAT TRANSFER
Field(s)/Group(s):
Fluid Mechanics
Keyword(s):
COMPUTER AIDED ANALYSIS
Report Date:
1972 Oct 01