LOW DENSITY HIGH TEMPERATURE DYNAMICS.
Abstract
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.
Document Details
- Document Type
- Technical Report
- Publication Date
- Nov 01, 1963
- Accession Number
- AD0631665
Entities
People
- J. J. Smolderen