Hypersonic reactive flowfield results are presented for the flow about an axisymmetric representation of a three-dimensional aeroassisted vehicle using the viscous shock-layer (VSL) and Navier-Stokes (NS) equations for low- and high-altitude entry conditions, respectively. Solutions are limited to the stagnation region. The NS results have been obtained by employing the surface recombination boundary condition for an 11-species air model, whereas the VSL calculations are carried out by using a 5-species model. Three widely used surface recombination rate models are implemented with these two flowfield calculation procedures. The low-density (or high altitude) NS solutions are obtained with surface slip equations and compare quite well with the direct simulation Monte Carlo predictions. For higher densities (or lower altitudes), the no-slip VSL solutions are considered adequate. Results from this study highlight the effect of surface catalyticity on surface heating and electron number density.
Stagnation flowfield analysis for an aeroassisted vehicle
Journal of Spacecraft and Rockets ; 30 , 1
1993-02-01
Miscellaneous
No indication
English
Stagnation Flowfield Analysis for an Aeroassisted Vehicle
Online Contents | 1993
|Aeroassisted orbit transfer vehicle trajectory analysis
NTRS | 1988
|Aeroassisted Orbit Transfer Vehicle Trajectory Analysis
NTIS | 1988
|