Abstract
One of the problems associated with the development of high-enthalpy hypersonic test facilities hos been the determination of nozzle flow properties. This note presents a technique for determining the flow properties of air in an equilibrium, non-equilibrium, or frozen state using two test section measurements. A knowledge of two stagnation properties is required before the technique can be applied. The stagnation pressure can be measured, and reference 1 offers a method for determining stagnation enthalpy. Results of the calculations using the method of reference 1 are presented in reference 2 in a chart (chart 21) which can be readily used to determine the stagnation enthalpy from measurements of stagnation pressure, mass flow of air through the tunnel, and throat diameter.
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