THEORY ON AFTERBURNING IN A LOW-ALTITUDE ROCKET EXHAUST PLUME.
Abstract
An improved aerodynamic model is proposed for the exhaust plume issuing from a low-altitude rocket nozzle exit into quiescent ambient air in which chemical reactions and compressibility predominate. The model is based on the presently available knowledge and established aerodynamic principles for the various flow regimes involved. The major assumptions made are individually substantiated by related experimental evidence in existing literature. A theoretical analysis is carried over the whole flow region based on the Karman's integral approach to find solutions for the gross aerodynamic and thermodynamic behavior of the plume. Theory incorporating on empirically derived constants provides the required radial distribution function for the integration. Solutions are obtained for the velocity, density, temperature and chemical composition fields for extended regions of the plume. These results will provide the much needed framework for the understanding of the elements which contribute to the phenomenon of radar attenuation of rocket exhaust plumes. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Oct 15, 1968
- Accession Number
- AD0679664
Entities
People
- Richard Shao-lin Lee
- W. W. Balwanz
Organizations
- United States Naval Research Laboratory