Date of Award

Spring 1980

Document Type


Degree Name

Doctor of Philosophy (PhD)


Mechanical & Aerospace Engineering


Mechanical Engineering

Committee Director

Surendra N. Tiwari

Committee Member

Kenneth Sutton

Committee Member

Charles H. Cooke

Committee Member

Wynford Harries

Committee Member

Robert L. Ash


The influence of nonequilibrium radiative energy transfer and the effect of probe configuration changes on the flow phenomena around a Jovian entry body is investigated. The radiating shock-layer flow is assumed to be axisymmetric, viscous, laminar and in chemical equilibrium. The radiative transfer equations are derived under nonequilibrium conditions which include multi-level energy transitions. The equilibrium radiative transfer is calculated with an existing nongray radiation model which accounts for molecular band, atomic line and continuum transitions. The nonequilibrium results are obtained with and without ablation injection in the shock layer. The nonequilibrium results are found to be influenced greatly by the temperature distribution in the shock layer. In the absence of ablative products, the convective and radiative heating to the entry body are reduced significantly under nonequilibrium conditions. The influence of nonequilibrium is found to be greater at higher entry altitudes. With coupled ablation and carbon phenolic injection, 16 chemical species are used in the ablation layer for radiation absorption. Equilibrium and nonequilibrium results are compared under peak heating conditions. For the study of the probe shape change effects, the initial body shapes considered are 45-degree sphere cone, 35-hyperboloid, and 45-degree ellipsoid. In all three cases, the results indicate that the shock-layer flowfield and heat transfer to the body are influenced significantly by the probe shape change. The effect of shape change on radiative heating of the after-bodies is found to be considerably larger for the sphere cone and ellipsoid than for the hyperboloid.