Physical characteristics and test conditions of an ethylene-heated high-temperature jet

Roland D. English, Abraham Spinak, Eldred H. Helton
Jan 1958

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 to produce a supersonic stream in which tests may be made at stagnation temperatures up to nearly 5,000 degrees R. The stagnation temperature and static and stagnation pressure profiles have been measured at center-line stagnation temperatures up to about 3,600 degrees R. The thermal properties 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 2.03. Reynolds numbers based on a length of 1 foot varied from about 14 x 10-to-the-sixth at a stagnation temperature of 1,000 degrees R to about 2 x 10-to-the-sixth at a stagnation temperature of nearly 5,000 degrees R. Corresponding Prandtl numbers varied between 0.721 and 0.622.

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