NASA NTRS · 19750019999
Hypersonic research engine project. Phase 2: Aerothermodynamic integration model development, data item no. 55-4-21
Abstract
The design and development of the Aerothermodynamic Integration Model (AIM) of the Hypersonic Research Engine (HRE) is described. The feasibility of integrating the various analytical and experimental data available for the design of the hypersonic ramjet engine was verified and the operational characteristic and the overall performance of the selected design was determined. The HRE-AIM was designed for operation at speeds of Mach 3 through Mach 8.
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Jilly, L. F.. 1975-05-19. Hypersonic research engine project. Phase 2: Aerothermodynamic integration model development, data item no. 55-4-21. https://ntrs.nasa.gov/citations/19750019999
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