Simulation of entry flight flowfield over four probe vehicles in pioneer-venus mission

Masanori Takahashi, Keisuke Sawada

Research output: Contribution to conferencePaper

8 Citations (Scopus)

Abstract

A trajectory-based analysis of the aerodynamic heating environment for the Pioneer-Venus four probe vehicles is attempted to reproduce the flight data of temperature histories. In order to give a consistent wall boundary condition, a thermo-chemical nonequilibrium computational fluid dynamics code is coupled with a charring materials ablation code that characterizes the ablation product gas. It is shown that the higher heating rate at the frustum region can be reproduced if we assume the ablation product gas to be inherently turbulent. The calculated temperature histories at the thermocouple positions agree fairly well with the flight data for all four probe vehicles.

Original languageEnglish
Publication statusPublished - 2002 Dec 1
Event40th AIAA Aerospace Sciences Meeting and Exhibit 2002 - Reno, NV, United States
Duration: 2002 Jan 142002 Jan 17

Other

Other40th AIAA Aerospace Sciences Meeting and Exhibit 2002
CountryUnited States
CityReno, NV
Period02/1/1402/1/17

ASJC Scopus subject areas

  • Space and Planetary Science
  • Aerospace Engineering

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    Takahashi, M., & Sawada, K. (2002). Simulation of entry flight flowfield over four probe vehicles in pioneer-venus mission. Paper presented at 40th AIAA Aerospace Sciences Meeting and Exhibit 2002, Reno, NV, United States.