DTIC ADA134035: Shock Tube Study of the pdf

DTIC ADA134035: Shock Tube Study of the

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The goal of this project is to obtain data that will help identify the reaction mechanism and the ignition limits of aluminum at elevated temperatures and pressures. Formidable problems arise when attempting such measurements in rocket motors since conditions are unsteady and not easy to control. Therefore, it was decided to mount a pure aluminum sample to the end wall of a shock tube and to ignite the sample using a reflected shock wave. The pressures and temperatures that can be achieved (40 atm, 5000 K) are typical of rocket motor conditions and are much higher than those obtained in previous studies using incident shock waves in conventional shock tubes. The aluminum sample reacts with a test gas in which the proportions of nitrogen, hydrogen, oxygen and chlorine are the same as found in ammonium perchlorate

• Creator/s: Defense Technical Information Center
• Date: 8/1/1983
• Year: 1983
• Book Topics/Themes: DTIC Archive, Driscoll, J. F., MICHIGAN UNIV ANN ARBOR GAS DYNAMICS LABS, *Aluminized propellants, *Combustion, *Ignition, *Shock tubes, Chemical reactions, Combustion products, High temperature, Aluminum, Oxidation, Spectroscopy, Reaction kinetics, Experimental design

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