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

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

Author
Jilly, L. F.
Published
May 19, 1975.
Physical Description
1 electronic document
Online Version

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Restrictions on Access
Unclassified, Unlimited, Publicly available.
Free-to-read Unrestricted online access
Summary
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.
Other Subject(s)
Collection
NASA Technical Reports Server (NTRS) Collection.
Note
Document ID: 19750019999.
Accession ID: 75N28071.
AIRESEARCH-AP-75-11133.
NASA-CR-132654.
Terms of Use and Reproduction
No Copyright.
View MARC record | catkey: 15739338