A 1-lb-thrust rocket engine was tested to determine plume symmetry and Mach number contours at 400,000-ft altitude. Total pressure surveys were made with and without a flat plate in the plume. The tests without the plate indicated the plume was symmetrical, and measured results compared well with computed values. In tests with the plate, the shock interaction and boundary-layer buildup on the plate were measured. (Author)
Investigation at High Altitudes of Rocket Exhaust Plume Symmetry and Interaction with a Plate with a Scaled MOL Thruster
1969
35 pages
Report
No indication
English
Combustion & Ignition , Fluid Mechanics , Rocket Engines & Motors , Exhaust gases , Attitude control systems , Axially symmetric flow , Pitot tubes , Rocket nozzles , Interactions , Boundary layer , Liquefied gases , Nitrogen , Helium , Cryogenics , Combustion chambers , High altitude , Flow fields , Computers , Liquid propellant rocket engines , Bipropellants , Methyl hydrazines , Test equipment , Pressure , Manned spacecraft , Thrust , Plumes(Radiation) , Hydrazine/monomethyl , Impingement , Manned orbiting laboratories , Mmh , Mol(Manned orbiting laboratories) , Nitrogen oxide(No)
The Influence of Particulates on Thruster Plume / Shock Layer Interaction at High Altitudes
British Library Conference Proceedings | 2005
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