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
      Fluid Mechanics
      Jet and Gas Turbine Engines

Distribution Statement : APPROVED FOR PUBLIC RELEASE