NASA NTRS · 19720018064
Hypersonic research engine project. Phase 2: Aerothermodynamic integration model development
Abstract
The analytical effort was directed toward (1) analyzing the latest inputs of possible test conditions and their impact on hardware; (2) review structural capabilities of the AIM unit; (3) analyzing coolant flow paths, heat transfer, and associated problems relative to the cowl leading edge tip section; and (4) redefining requirements of flow-calibrating the air-metering duct.
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Jilly, L. F.. 1971-01-06. Hypersonic research engine project. Phase 2: Aerothermodynamic integration model development. https://ntrs.nasa.gov/citations/19720018064
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