A bipropellant rocket engine plume contamination test program was conducted in the AEDC Aerospace Chamber (10V). A 5-lbf-thrust rocket engine, burning MMH as the fuel and N2O4 as the oxidizer, was operated over a range of engine operating parameters in a cryogenically pumped vacuum chamber where the background pressure was maintained below 0.00001 torr. Using the electron beam fluorescence technique, species number densities and rotational temperture were measured in both the forward- and back-flow region of the plume exhaust. Additionally, Mie scattering measurements were performed for the forward-flow regions of the plume exhaust. (Author)
Bipropellant Engine Plume Contamination Program. Volume II. Chamber Measurements. Phase II
1979
115 pages
Report
Keine Angabe
Englisch
Air Pollution & Control , Exhaust plumes , Liquid propellant rocket engines , Bipropellants , Contamination , Nitrogen compounds , Tetroxides , Methyl hydrazines , Liquid rocket propellants , Mie scattering , Electron beams , Fluorescence , Vacuum chambers , Air pollution , Liquid rocket oxidizers , Liquid rocket fuels , Nitrogen peroxide