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Propulsion System Flow Stability Program (Dynamic). Part VIII. Model for Predicting Compressor Performance with Combined Circumferential and Radial Distortion - Computer Program.

AD851903

Publication Date	1968
Personal Author	Novak, R. A.; Hearsey, R. M.
Page Count	312
Abstract	The part describes in detail a computer program designed to enable the performance of axial flow compressors operating under asymmetric inlet conditions to be predicted. The underlying theory is given in Part VII; a comparison between results obtained and experimental data is made in Part IX. The report is divided into a number of sections, the principal ones being those giving a Functional Discription of the program, and an Operational Description of the program. The Functional Description is intended to enable the program to be used. The Operational Description of the program is intended to enable the methods used in the program to be understood in detail, hence allowing the program to be modified if desired. (Author)
Keywords	Turbofan engines Axial flow compressors Turbojet inlets Aerodynamic characteristics Flow separation Flow charting Mathematical models Predictions Computer programs Performance(Engineering) Asymmetric bodies Engine surge Distortion Stability Gas flow Aircraft engines Gas turbines Tf-30 engines Tf-30-p-3 engines
Source Agency	Non Paid Delimited ADS
NTIS Subject Category	81D - Jet & Gas Turbine Engines 46B - Fluid Mechanics
Corporate Authors	North American Rockwell Corp Los Angeles Calif Los Angeles Div
Supplemental Notes	See also Part 7, AD-851 902 and Part 9, AD-851 904. Prepared in cooperation with Northern Research and Engineering Corp., Cambridge, Mass. and General Motors Corp., Indianapolis, Ind. Allison Div., Rept. no. EDR-5908-Pt 8.
Document Type	Technical Report
Title Note	Final technical rept. 20 Jun 67-30 Sep 68 on Phase 1.
NTIS Issue Number	197701
Contract Number	F33615-67-C-1848

Propulsion System Flow Stability Program (Dynamic). Part VIII. Model for Predicting Compressor Performance with Combined Circumferential and Radial Distortion - Computer Program.

Propulsion System Flow Stability Program (Dynamic). Part VIII. Model for Predicting Compressor Performance with Combined Circumferential and Radial Distortion - Computer Program.
AD851903

Publication Date	1968
Personal Author	Novak, R. A.; Hearsey, R. M.
Page Count	312
Abstract	The part describes in detail a computer program designed to enable the performance of axial flow compressors operating under asymmetric inlet conditions to be predicted. The underlying theory is given in Part VII; a comparison between results obtained and experimental data is made in Part IX. The report is divided into a number of sections, the principal ones being those giving a Functional Discription of the program, and an Operational Description of the program. The Functional Description is intended to enable the program to be used. The Operational Description of the program is intended to enable the methods used in the program to be understood in detail, hence allowing the program to be modified if desired. (Author)
Keywords	Turbofan engines Axial flow compressors Turbojet inlets Aerodynamic characteristics Flow separation Flow charting Mathematical models Predictions Computer programs Performance(Engineering) Asymmetric bodies Engine surge Distortion Stability Gas flow Aircraft engines Gas turbines Tf-30 engines Tf-30-p-3 engines
Source Agency	Non Paid Delimited ADS
NTIS Subject Category	81D - Jet & Gas Turbine Engines 46B - Fluid Mechanics
Corporate Authors	North American Rockwell Corp Los Angeles Calif Los Angeles Div
Supplemental Notes	See also Part 7, AD-851 902 and Part 9, AD-851 904. Prepared in cooperation with Northern Research and Engineering Corp., Cambridge, Mass. and General Motors Corp., Indianapolis, Ind. Allison Div., Rept. no. EDR-5908-Pt 8.
Document Type	Technical Report
Title Note	Final technical rept. 20 Jun 67-30 Sep 68 on Phase 1.
NTIS Issue Number	197701
Contract Number	F33615-67-C-1848