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THE FAR FIELD OF A ROCKET EXHAUST JET AT LOW AND MODERATE ALTITUDES
GENERAL DYNAMICS/ASTRONAUTICS SAN DIEGO CA
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A method is given for predicting the flow field of a rocket exhaust plume at distances far removed from the nozzle exit at altitudes where afterburning of the exhaust is appreciable. The calculation combines a fluid mechanical analysis of turbulent mixing due to Libby with the adiabatic flame temperature calculation of Boynton and Neu. The eddy viscosity is determined from a consideration of conditions under which compressible turbulent flows appear to exhibit self-preserving behavior. Instructions are given for preparing input to two computer programs which are based on the analysis in the report. In two appendices, it is shown how the eddy viscosity constants may be derived from incompressible jet flow data and a comparison of the results of the present calculation with experimental wind-tunnel rocket exhaust behavior is given.
APPROVED FOR PUBLIC RELEASE