Abstract
The shock-induced combustion of hydrogen and ethylene, stabilized in a supersonic tunnel behind the Mach intersection of two oblique shock waves, was studied under the following conditions: Mach Number at the entrance of the test section: M 1 =2.4 or 3.3; Total temperature on the axis: 1200°K≤ T t1 ≤1600°K; Equivalence ratio on the axis: 0.1≤ r 1 ≤0.8 for hydrogen, and 0.8≤ r 1 ≤3 for ethylene. The flow-field parameters, without combustion, were derived from total temperature, totalpressure, and static pressure measurements. Data on combustion were obtained by means of flame-picture records, gas-sample analyses, and from measurements of temperature by the sodium line-reversal method. From the results, it can be concluded that: o (i) The measured values of the induction time are in good agreement with theoretical and experimental results of other investigators, which make any induction reaction upstream of the shock wave improbable. (ii) The flow expansion behind the shock wave may quench to shock-induced reactions; this assumption is supported by: the absence of a luminous flame close to the shock wave in spite of the combustion of small amounts of fuel; the presence of a two-stage flame in the case of ethylene, the reactions starting up again (after quenching) by flow recompression.
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