NavierStokes and viscous shocklayer solutions for radiating hypersonic flows
Abstract
Results are presented from the NavierStokes and viscous shocklayer (VSL) calculations with nonequilibrium and equilibrium chemistry, respectively. These calculations contain coupling to the Aerotherm radiation code RAD. A simplified form of the electron energy equation is used to obtain an electron temperature in the NavierStokes calculations. The radiation in the flowfield is calculated using this temperature. The NavierStokes code is used at high altitude only, whereas the VSL code is employed for the entire entry period to make estimates of the radiative and convective heating to the Fire II vehicle. Results from the NavierStokes code have also been compared with the predictions of Lee and Kawamura, who used graygas radiation model and thinlayer NavierStokes equations. Quite good agreement is obtained between the measured and computed values of radiative and convective heating from the VSL code in th mediumtolow altitude flight regime of the Fire II vehicle. At high altitudes, the NavierStokes calculations considerably overpredict the Fire II flight data for radiative intensity. This is attributed to the deficiencies in the Aerotherm radiation model when used for lowdensity flight conditions. This model contains the thermal equilibrium assumption and precludes accounting for the collisionlimiting phenomenon at high altitudes. Present NavierStokes calculations highlight the effect of these assumptions on radiative heating calculations for such conditions.
 Publication:

AIAA, 22nd Thermophysics Conference
 Pub Date:
 June 1987
 Bibcode:
 1987thph.confR....G
 Keywords:

 Aerothermochemistry;
 Hypersonic Flow;
 NavierStokes Equation;
 Radiant Heating;
 Shock Layers;
 Viscous Flow;
 Chemical Equilibrium;
 Chemical Reactions;
 Computational Fluid Dynamics;
 Orbit Transfer Vehicles;
 Fluid Mechanics and Heat Transfer