Accession Number : AD0503304
Title : Propulsion System Flow Stability Program (Dynamic). Part XIV. Propulsion System Stability Margin Performance Penalties for an RA-5C Aircraft.
Descriptive Note : Final technical rept. 20 Jun 67-30 Sep 68 on Phase 1,
Corporate Author : NORTH AMERICAN ROCKWELL CORP LOS ANGELES CALIF LOS ANGELES DIV
Personal Author(s) : Tyson,Ray M.
Report Date : DEC 1968
Pagination or Media Count : 73
Abstract : Steady state propulsion system and aircraft performance penalties due to control margins required for transient operation were studied for the RA-5C aircraft/J79 engine configuration. Significant performance gains were made when these margins could be reduced and a smaller turbine used. (Author)
Descriptors : (*TURBOJET ENGINES, *ATTACK BOMBERS), (*FLOW FIELDS, STABILITY), SUBSONIC CHARACTERISTICS, SUPERSONIC CHARACTERISTICS, OPTIMIZATION, PERFORMANCE(ENGINEERING), TURBOJET INLETS, TEMPERATURE, COMPRESSORS, CONTROL, MISSION PROFILES, ANALYSIS, COMPUTER PROGRAMS, COMPRESSOR STATORS, GAS TURBINES, WEIGHT, REDUCTION, ENGINE SURGE, AFTERBURNERS, CONTROL SYSTEMS (U) RECONNAISSANCE AIRCRAFT, STALLING
Subject Categories : Bombers
Attack and Fighter Aircraft
Patrol and Reconnaissance Aircraft
Jet and Gas Turbine Engines
Distribution Statement : APPROVED FOR PUBLIC RELEASE