AN ADVANCED METHOD FOR PREDICTING THE PERFORMANCE OF HELICOPTER PROPULSION SYSTEM EJECTORS

A new analytical technique for predicting ejector throat static pressu re while predicting ejector mass flow ratio is presented. Ejector mode ling was performed using integral forms of the governing conservation equations for compressible flow, A new correction factor, named the se condary flow correction factor, was devised to balance the pressure fo rces on the ejector control volume while accounting for real ejector s ystem losses. Excellent agreement was obtained when results of high an d low pressure ratio ejector tests were compared to theory using the s econdary flow correction factor.