Accession Number:

AD0856259

Title:

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

Descriptive Note:

Technical rept. 23 Jul-5 Sep 68 on Phase II,

Corporate Author:

NORTH AMERICAN ROCKWELL CORP LOS ANGELES CA LOS ANGELES DIV

Personal Author(s):

• Alfano, David L.

Report Date:

1969-06-01

Pagination or Media Count:

399.0

Abstract:

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. Author

Descriptors:

• *JET FIGHTERS
• *TURBOJET EXHAUST NOZZLES
• TURBOFAN ENGINES
• CAPTIVE TESTS
• DUCTED BODIES
• SHROUD RINGS
• THRUST
• PREDICTIONS
• NOZZLE GAS FLOW
• CONFIGURATIONS

Subject Categories:

• Attack and Fighter Aircraft
• Jet and Gas Turbine Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE