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:

1968-12-01

Pagination or Media Count:

73.0

Abstract:

Steady state propulsion system and aircraft performance penalties due to control margins required for transient operation were studied for the RA-5C aircraftJ79 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