Analysis of the Chemically-Reactive Mixing Region Between a Turbulent Rocket Exhaust and a Confined Air Stream
Abstract
A theoretical analysis was developed for predicting the flow properties in the mixing region between a particle-laden, turbulent rocket exhaust and a surrounding air stream. It was assumed that the turbulent boundary layer equations, modified to account for particles, were valid within the mixing region. The phenomenological model employed for the turbulent transport coefficients is discussed in detail and compared with various other models. The solution of the partial differential equations was obtained by transforming the equations using the von Mises transformation, solving the resulting equations utilizing a computer program developed for the SRU 1107. Results from the computer program were successfully compared with experimental results obtained from air-augmentation, free jet, and fuel injection experiments. Output data from the computer program comprises velocity, temperature, density, species concentration, and Mach number profiles at various axial locations along the mixing region.
Document Details
- Document Type
- Technical Report
- Publication Date
- Mar 03, 1965
- Accession Number
- ADB011931
Entities
People
- Donald L. Emmons
Organizations
- Boeing