Abstract
A numerical method has been developed for calculating the flow in intermediate altitude rocket exhaust plumes. The method used is a modification of the Lagrangian finite-difference technique developed by Boynton and Thomson for calculating the flow in high-altitude rocket exhaust plumes. Their technique has been extended to intermediate altitude rocket exhaust plumes by incorporating chemical nonequilibrium and turbulent transport capabilities into the analysis. Using this new technique, the flow in a Thor exhaust plume at an intermediate altitude of 150,000 ft is calculated. The results are compared with those obtained through the application of an in viscid, nonreacting method of characteristics calculation.
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