The one-dimensional flow equation for mass flow through the throat of a supersonic nozzle has been modified for use with real gas values of gamma and compressibility. Curve fits for gamma and Z and a simple iteration scheme have been developed for use with air and nitrogen over a temperature range of 300 to 6000 deg. K and a pressure of 10 to 100 atm. With this approach the sonic throat method can be used with the most recent gas tables to determine high temperature wind tunnel supply temperatures or enthalpies. (Author).

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