Accession Number : AD0866554
Title : Propulsion System Flow Stability Program (Dynamic). Part VII. Description and Results of a Program for Predicting Performance of a Fan/Compressor with Arbitrary Flow Division.
Descriptive Note : Final technical rept. 1 Oct 68-1 Dec 69 on Phase 2,
Corporate Author : NORTH AMERICAN ROCKWELL CORP LOS ANGELES CA LOS ANGELES DIV
Personal Author(s) : Jansen, Willem
Report Date : FEB 1970
Pagination or Media Count : 54
Abstract : The analytic concept and capabilities of a computer program for predicting performance of a fan/compressor with arbitrary flow division are described in this volume, Part VII. It further presents comparisons of YTF-33 fan/compressor test data with program predictions. Finally, the results of parametric studies to evaluate the effects of the front fan and the splitter lip on the compressor performance at different bypass ratios are presented. It was concluded that the program is a valuable tool for predicting fan/compressor performance at off-design conditions, and for determining modifications that would improve performance. (Author)
Descriptors : (*RECONNAISSANCE AIRCRAFT, TURBOJET ENGINES), (*TURBOJET ENGINES, AXIAL FLOW COMPRESSORS), (*AXIAL FLOW COMPRESSORS, FLOW SEPARATION), TURBOFAN ENGINES, TURBINE PARTS, TURBOJET INLETS, FLOW FIELDS, TURBOJET EXHAUST NOZZLES, MATHEMATICAL MODELS, PREDICTIONS, COMPUTER PROGRAMMING, ADVANCED WEAPONS.
Subject Categories : Patrol and Reconnaissance Aircraft
Jet and Gas Turbine Engines
Distribution Statement : APPROVED FOR PUBLIC RELEASE