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

AD856259

Publication Date	1969
Personal Author	Alfano, D. L.
Page Count	399
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)
Keywords	Jet fighters Turbojet exhaust nozzles Turbofan engines Captive tests Ducted bodies Shroud rings Thrust Predictions Nozzle gas flow Configuration
Source Agency	Non Paid Delimited ADS
NTIS Subject Category	81D - Jet & Gas Turbine Engines 51C - Aircraft
Corporate Authors	North American Rockwell Corp Los Angeles Calif Los Angeles Div
Supplemental Notes	See also Part 1, AD-503 305, and Part 5, AD-855 767.
Document Type	Technical Report
Title Note	Technical rept. 23 Jul-5 Sep 68 on Phase II.
NTIS Issue Number	197701
Contract Number	F33615-67-C-1829

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

Propulsion System Integration and Test Program (Steady State). Part II. Shared Exit Ejector Nozzle Static Tests.
AD856259

Publication Date	1969
Personal Author	Alfano, D. L.
Page Count	399
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)
Keywords	Jet fighters Turbojet exhaust nozzles Turbofan engines Captive tests Ducted bodies Shroud rings Thrust Predictions Nozzle gas flow Configuration
Source Agency	Non Paid Delimited ADS
NTIS Subject Category	81D - Jet & Gas Turbine Engines 51C - Aircraft
Corporate Authors	North American Rockwell Corp Los Angeles Calif Los Angeles Div
Supplemental Notes	See also Part 1, AD-503 305, and Part 5, AD-855 767.
Document Type	Technical Report
Title Note	Technical rept. 23 Jul-5 Sep 68 on Phase II.
NTIS Issue Number	197701
Contract Number	F33615-67-C-1829