Numerical Solution of the Navier-Stokes Equations for Rocket Plumes at 120 km Altitude
Final technical rept.
APPLIED THEORY INC LOS ANGELES CA
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Results are presented of a first-principle calculation of steady flow to a distance of 300 ft aft of an Atlas booster emitting exhaust gases. Agreement between the air shock locus reported and that predicted by the simpler model of Boynton, improves with distance from the vehicle. Boyntons air-plume shock radius is smaller by factors of 2.2, 1.8 and 1.5, at distances of 100, 200, and 300 ft, respectively, aft of the vehicle. For the jet shock, the corresponding ratios at the same three downstream locations are 1.5, 1.1 and 1. 0, respectively. No evidence of Helmholtz instability was found in the calculated flow-field.
- Fluid Mechanics
- Ground Support Systems and Facilities for Space Vehicles