Shock Shapes in Gaseous Secondary Injection
ARMY MISSILE RESEARCH DEVELOPMENT AND ENGINEERING LAB REDSTONE ARSENAL AL GUIDANCE AND CONTROL DIRECTORATE
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The objective of this study was to develop a technique of predicting shock shapes and wall shock traces encountered in secondary injection into a conical rocket nozzle. The analysis is based on an analogy with Sakurais second order blast wave theory, with allowance for axial variation in the free stream Mach number in the primary nozzle. Model tests indicate spreading of the shock adjacent to the wall slightly higher than expected. A procedure for shock prediction is presented based on one empirically determined constant. Independence of side forces in perpendicular secondary injection planes under conditions of shock intersection was experimentally verified.
- Fluid Mechanics
- Rocket Engines