Propulsion System Flow Stability Program (Dynamic). Part VIII. Model for Predicting Compressor Performance with Combined Circumferential and Radial Distortion - Computer Program.
Report Number: AFAPL TR 68-142 Part VIII Author(s): Novak, R. A.; Hearsey, R. M. Corporate Author: Northern Research and Engineering Corporation Laboratory: Air Force Aero Propulsion Laboratory Date of Publication: 1968-12 Pages: 304 Contract: F333615-67-C-1848 AD Number: AD0851903
Abstract: The report 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.
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This report has the following parts/volumes:
Propulsion System Flow Stability Program (Dynamic). Part XII. Unsteady Combustion in Duct Burners and Afterburners
AFAPL TR 68-142 Part XII
Propulsion System Flow Stability Program (Dynamic). Part XVI. Survey of Sensors Applicable to the Control of Aircraft Propulsion Systems
AFAPL TR 68-142 Part XVI
Propulsion System Flow Stability Program (Dynamic). Part XVII. Propulsion System Simulation Digital Computer Program Format and Routines
AFAPL TR 68-142 Part XVII
Propulsion System Flow Stability Program (Dynamic). Part XX. Computer Programs for the Root Locus Analysis of Linearized Turbojet and Turbofan Control Systems
AFAPL TR 68-142 Part XX