A new thermal protection system by opposing jet for reusable launch vehicles

Kentaro Hayashi, Shigeru Aso, Yasuhiro Tani

Research output: Contribution to conferencePaperpeer-review

1 Citation (Scopus)

Abstract

A numerical study on a reduction of aerodynamic heating by opposing jet in supersonic flow has been conducted. Flow field around a hemisphere model is calculated in supersonic free stream of Mach number 3.98 and the coolant gas is injected through the sonic nozzle at the nose of the model. In numerical analysis, axisymmetric Navier-Stokes equations are solved by an implicit finite difference method, and k-co turbulence model is used. According to the investigation of various conditions of opposing jet, important phenomena of flow field and some effective jet conditions are found. It becomes clear that a performance of the thermal protection system by opposing jet is greatly affected by jet conditions.

Original languageEnglish
Pages5322-5332
Number of pages11
Publication statusPublished - Dec 1 2005
EventInternational Astronautical Federation - 56th International Astronautical Congress 2005 - Fukuoka, Japan
Duration: Oct 17 2005Oct 21 2005

Other

OtherInternational Astronautical Federation - 56th International Astronautical Congress 2005
CountryJapan
CityFukuoka
Period10/17/0510/21/05

All Science Journal Classification (ASJC) codes

  • Space and Planetary Science
  • Aerospace Engineering

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