Calculation of hypersonic flow with ablation for Pioneer-Venus probe

Yoshinori Izawa, Keisuke Sawada

Research output: Contribution to conferencePaperpeer-review

2 Citations (Scopus)

Abstract

A computational fluid dynamics (CFD) code is developed to calculate the convective heating rate over the Pioneer-Venus Day Probe vehicle with ablation during its entry flight into the planet Venus. The Venusian atmosphere is assumed a pure CO2 gas, and two-temperature description of nonequilibrium thermochemical state is employed- A material thermal response code named super charring material ablation (SCMA) is coupled with the CFD code to give a consistent wall boundary condition. In order to explain the higher temperature at frustum region shown in the flight data, ablation gas is assumed to be inherently turbulent and is described by the injection-induced turbulence model developed earlier by Park. The calculation gives a consistent and converged solution for typical flight conditions along the trajectory. The higher heating rate at frustum region is indicated.

Original languageEnglish
DOIs
Publication statusPublished - 2000
Event38th Aerospace Sciences Meeting and Exhibit 2000 - Reno, NV, United States
Duration: 2000 Jan 102000 Jan 13

Other

Other38th Aerospace Sciences Meeting and Exhibit 2000
Country/TerritoryUnited States
CityReno, NV
Period00/1/1000/1/13

ASJC Scopus subject areas

  • Space and Planetary Science
  • Aerospace Engineering

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