Numerical Solution of the Navier-Stokes Equations for Rocket Plumes at 120 km Altitude
Abstract
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. Boynton's 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.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jul 01, 1974
- Accession Number
- AD0784332
Entities
People
- J. G. Trulio
- L. C. Himmell