Numerical study of thermal protection system by opposing jet

Kentaro Hayashi, Shigeru Aso, Yasuhiro Tani

研究成果: Contribution to conferencePaper査読

64 被引用数 (Scopus)

抄録

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 3.96 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-ω turbulence model is used. Significant decreases of surface heat flux are observed and opposing jet is proved to be effective on aerodynamic heating reduction around a stagnation region of the blunt body. In our previous study, experiments on the reduction of aerodynamic heating by opposing jet in supersonic flow were conducted in wind tunnel. The result of numerical analysis shows good agreement with experiment. Numerical results show that the recirculation region plays an important role for the reduction of heat flux. For the reduction of the aerodynamic heating, it is effective to cover the body surface with the cool jet flow and to form strong circulation region.

本文言語英語
ページ11641-11648
ページ数8
出版ステータス出版済み - 12 1 2005
イベント43rd AIAA Aerospace Sciences Meeting and Exhibit - Reno, NV, 米国
継続期間: 1 10 20051 13 2005

その他

その他43rd AIAA Aerospace Sciences Meeting and Exhibit
国/地域米国
CityReno, NV
Period1/10/051/13/05

All Science Journal Classification (ASJC) codes

  • 工学(全般)

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