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adiabatic compression ignition annular clearance appear approximately assumed average buffer compression ignition temperature condition conducted CORNELL UNIVERSITY curve data of Fig degree determine detonation diameter diaphragm distance drum camera record duration elevated initial temperatures end plate exist experimental flow flush gage gas bottle gas mixtures initially Graduate School hole Incident shock initially at room inner wall Irregularities known Limit of Ignition Lower Limit means measured mechanism nition obtained occur One-dimensional oscill oscilloscope performed photographed pick-up plug points premixed present Pressure probes Ratio of specific reflected shock region reported results are plotted room temperature set of test shock tube shock velocity shook wave signature SKETCH sliding space-time diagram specific heats strength sweep tables thereby thesis three months Thyratron trial and error trigger tube wall uniform shock uniform temperature whioh whloh window sections