NASA NTRS · 19720018063
Hypersonic research engine project. Phase 2: Aerothermodynamic integration model development
Abstract
The analytical effort was directed towards (1) completing the design of the combustor exit instrumentation assembly, (2) analyzing the coolant flow distribution of the cowl leading edge tip section, (3) determining effects of purge gas pressure on AIM performance analysis, and (4) analyzing heat transfer and associated stress problems related to the cowl leading edge tip section and the nozzle shroud assembly for test conditions.
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Jilly, L. F.. 1970-10-15. Hypersonic research engine project. Phase 2: Aerothermodynamic integration model development. https://ntrs.nasa.gov/citations/19720018063
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