THE EFFECTS OF BASE BLEED AND SUSTAINER ROCKET NOZZLE DIAMETER AND LOCATION ON THE BASE DRAG OF A BODY OF REVOLUTION WITH CONCENTRIC BOOST AND SUSTAINER ROCKET NOZZLES
ARMY MISSILE RESEARCH DEVELOPMENT AND ENGINEERING LAB REDSTONE ARSENAL AL ADVANCED SYSTEMS CONCEPTS OFFICE
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A concentric arrangement of boost and sustainer rocket nozzles was investigated to determine the effects of base bleed and the effects of sustainer nozzle diameter and relative longitudinal position on the base drag of the body during sustainer operation. The results of the investigation indicate that the jet-on base drag of a body can be significantly reduced by the use of base bleed and nozzle arrangement, and that the jet-on base drag is a function of the jet thrust. The data presented are based on the results of tests in the Aberdeen Ballistic Research Laboratories 13 by 15 inch supersonic wind tunnel at Mach numbers of 2.0 and 2.5. The model tested had sustainer nozzle-to-base diameter ratios of 0.10, 0.20, and 0.30, and boost nozzle-to-base diameter ratio of 0.80. The sustainer nozzle was tested at longitudinal positions between 0.60 calibers aft to 0.98 calibers forward of the base.
- Guided Missile Dynamics, Configurations and Control Surfaces
- Rocket Engines