NASA NTRS · 19720018061
Hypersonic research engine project. Phase 2: Structures and cooling development
Abstract
The flightweight components were adapted to form the basic engine assembly. The water cooled test adapters for use in wind tunnel tests were fabricated. Commercially available valves were selected for the coolant control system. The simplification of the temperature control concept and of the absence of weight and volume constraints made it possible to use these valves. Various calibration tests are also discussed.
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Jilly, L. F.. 1970-09-01. Hypersonic research engine project. Phase 2: Structures and cooling development. https://ntrs.nasa.gov/citations/19720018061
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