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Propulsion System Integration and Test Program (Steady State). Part II. Shared Exit Ejector Nozzle Static Tests

Report Number: AFAPL TR 69-44 Part 02
Author: Alfano, David L.
Corporate Author: North American Rockwell Corp Los Angeles CA Los Angeles Div
Laboratory: Air Force Aero Propulsion Laboratory
Date of Publication: 1969-06
Pages: 371
Contract: F33615-67-C-1829
Project: None Given
AD Number: AD0856259

A program for designing and conducting tests on a shared exit ejector nozzle was formulated to provide experimental verification of available analytic techniques, where applicable, and to provide data at those conditions where analytic techniques were not applicable so that this nozzle concept could be evaluated. The test plan was formulated around the complete spectrum of engine cycle data for an Integrated Propulsion System Tactical Fighter. Results from this test program indicate that the reliability of the available analytic techniques for predicting nozzle performance is dependent on an accurate estimate of the internal losses and aerodynamic flow areas involved.

Lockheed Martin Missiles & Fire Control
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