Shock Tube Study of the Ignition and Combustion of Aluminum.
Final rept. 11 Jun 79-10 Mar 82,
MICHIGAN UNIV ANN ARBOR GAS DYNAMICS LABS
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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.
- Test Facilities, Equipment and Methods
- Combustion and Ignition
- Solid Rocket Propellants