Numerical Study on Aerodynamic Heating Reduction by Opposing Jet

• Hayashi, Kentaro

  Department of Aeronautics and Astronautics : Graduate Student

• 麻生, 茂

  Department of Aeronautics and Astronautics : Professor

• 谷, 泰寛

  Department of Aeronautics and Astronautics : Assistant Professor

抄録

A numerical study on a reduction of aerodynamic heating by opposing jet in supersonic and hypersonic flow has been conducted. Flow field around a hemisphere model is calculated in the free stream of Mach number of 4 ands 8. The coolant gas is injected through the nozzle at the nose of the model. In numerical analysis, axisymmetric Navier-Stokes equations are solved with k-ω turbulence model. Flow structures at various conditions are investigated and flow mechanisms of reduction of aerodynamic heating are revealed. Also optimal jet conditions for the reduction of aerodynamic heating are obtained. 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.

収録刊行物

• 九州大学工学紀要

  九州大学工学紀要 66 (1), 39-54, 2006-03

  九州大学大学院工学研究院

キーワード

• Aerodynamic heating
• Jet
• Supersonic flow
• Numerical analysis

詳細情報

• CRID: 1050580007680988160
• NII論文ID: 110004808594
• NII書誌ID: AA11481788
• HANDLE: 2324/3293
• 本文言語コード: en
• 資料種別: departmental bulletin paper
• データソース種別:
  • IRDB
  • CiNii Articles
  • KAKEN