A Calculating Method for Optimum Performance of Supersonic Ejectors

A calculating method is developed to analyze optimum performance of supersonic ejectors under the assumptions that the mixing of the primary flow with the secondary one is done at constant pressure, and that a normal shock atays at the ejector throat. Since the method is formulated in terms of enthalpy, it is applicable to arbitrary primary and secondary gases. The compression ratio of the secondary gas is plotted against the throat area ratio for various stagnation pressure ratios of the primary and secondary flows. For the purpose of verification of the present method, the calculated results are compared with experimental results, and it is shown that the present method is effective to determine the optimum ejector performance in the case that the secondary mass flow rate and the primary stagnation pressure are given