Abstract
Experimental studies pertinent to axisymmetric, sudden-expansion dump combustor configurations for integral rocket-ramjet missiles have been performed under cold flow test conditions. These studies have included surface flow visualization, measurements of total and static pressures, and gas sampling within a representative combustor duct. Flow visualization tests, using a surface oil flow technique, vividly demonstrated the complex nature of the flow recirculation region downstream of the dump station. Gas concentration measurements of simulated fuel-air mixing were made in the combustor duct using an on-line gas analysis system with a quadrupole mass spectrometer. Combustor flowfield studies were made for test configurations with and without mechanical flameholding devices. Direct correlations between cold flow mixing data and measurements of combustion efficiency from direct-conned ramburner tests were made as a function of combustor Sen«fh-todiameter ratio.
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