Hypersonic research engine project. Phase 2: Aerothermodynamic integration model development, data item no. 55-4-21

Article

Hypersonic research engine project. Phase 2: Aerothermodynamic integration model development, data item no. 55-4-21

L. F. Jilly-1975-05-19-NASA STI Repository (National Aeronautics and Space Administration)

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TL;DRAbstract

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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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.

Keywords

Hypersonic speedMach numberAerospace engineeringRamjetHypersonic flightAero engineAerodynamicsEngineering

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