LOW DENSITY HIGH TEMPERATURE DYNAMICS.
Annual summary rept. 1 Oct 62-30 Sep 63,
TRAINING CENTER FOR EXPERIMENTAL AERODYNAMICS RHODE-SAINT-GENESE (BELGIUM)
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A low density continuous hypersonic wind tunnel was built and acceptance and preliminary calibration tests were completed. The first runs were made using a free jet, exhausting from a circular sonic orifice, with stagnation pressure in the range from 40 to 150 microns Hg. The test chamber pressure varied between 1, 5 and 6 microns Hg in these tests. No heater was used. A rather complete set of pressure measuring equipment was used in these tests, as well as a simple, axial traverse mechanism. Design of more advanced instrumentation and construction of a two degrees of freedom traversing gear are in progress. Performance and characteristics of the pumping system and vacuum tank of the wind tunnel are discussed.
- Test Facilities, Equipment and Methods