In order to investigate the effects of high temperatures incurred at hypersonic speeds, an ethylene-heated high-temperature jet has been developed at the Langley Pilotless Aircraft Research Station at Wallops Island, Va. The jet utilizes the combustion of ethylene (c2H4)nto produce a supersonic stream in which tests may be made at stagnation temperatures up to nearly 5,000° R. The stagnation temperature and static and stagnation pressure profiles have been measured at center-line stagnation temperatures up to about 3,600° R. The thermal prop¬erties of the exhaust gas and flow conditions in the test section have been calculated. The results show the test section Mach number to be about 2.05- Reynolds numbers based on a length of 1 foot varied from about 14 x lO6 at a stagnation temperature of 1,000° R to about 2 x 106 at a stagnation temperature of nearly 50000 R. Corresponding Prandtl numbers varied between 0.721.and O.622.
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