Date of Award

Fall 1981

Document Type

Thesis

Degree Name

Master of Science (MS)

Department

Mechanical & Aerospace Engineering

Program/Concentration

Mechanical Engineering

Committee Director

Surendra N. Tiwari

Committee Member

James N. Moss

Committee Member

Robert L. Ash

Committee Member

John M. Kuhlman

Call Number for Print

Special Collections; LD4331.E56 C445

Abstract

The extent of convective and rad1ative heating for a Titan entry vehicle is invest1gated. The flow in the shock layer is assumed to be axisymmtric, steady, viscous, and compressible. It is further assumed that the gas is in chemical and local thermodynamic equilibrium and tangent slab approximation is used for the rad1ative transport. The effect of slip boundary conditions on the body surface and at the shock wave are included in the analysis of high altitude entry conditions. The implicit finite difference technique is used to .solve the viscous shock layer equations for a 45-degree sphere cone at zero angle of attack. Different compositions for the Titan's N2 + CH4 atmosphere are assumed and results are obtained for the entry conditions specified by the Jet Propuls1on Laboratory. The results indicate that the heat1ng rate, in general, increases w1th 1ncreasing N& concentration, Both convective and radiative heat1ng increase with increasing initial entry velocity. The radiative heating increases but the convective heating decreases with increasing body nose radius. The amount of CN concentration in the shock layer gas determines the extent of radiat1ve heating to the body. Radiative heating will be important for freestream gas composition with N2 concentration between 50% and 90%. For the atmospheric compositions of 99.5% N2 + 0.5f CH4 and 98/ N2 + 21. CH4, the radiative heating near the stagnation region is insignificant in comparison to the convective heating. The results indicate that the effect of the slip conditions is important when the altitudes are higher than 402.595 km. Therefore, both the body and shock slip conditions should be included in analyzing the aerothermal environment of the Titan aerocapture vehicle at higher entry altitudes.

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DOI

10.25777/16rz-eh16

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