Numerical Simulation of Thermal-Chemical Non-equilibrium and Radiating Hypersonic Flow

  • Yibin Wang
  • Ning Qin
  • Xueqiang Liu
Conference paper


When a reentry capsule flies at a high speed through the earth atmosphere, the temperature of the shock layer formed around it may become sufficiently high to emit a significant amount of radiation. The radiation emanates mainly from the inviscid region of the shock layer where the flow is highly dissociated and ionized. When the radiation passes through the cold boundary which is near the wall, the radiation is absorbed by the air, so that the boundary layer is heated, while the inviscid region is cooled.When the magnitude of the radiation involved is significant in comparison with the convective heat flux at the wall, the radiation must be considered in the calculation of the heat load to the vehicle. To solve this problem, a number of computational methods have been developed such as NONEQ[1], LORAN[2], RASLE[3] and SPRADIAN[4]. However, most of them can only be applied on the structured grids with simplified radiation models. This paper presents a computational method which can simulate both the thermal-chemical non-equilibrium and air radiation on the same unstructured grids at a high temperature situation in order to solve the hypersonic problem with complicated geometries.


Shock Layer Hypersonic Flow Atomic Line Thermal Protection System Cold Boundary 
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Copyright information

© Springer-Verlag Berlin Heidelberg 2012

Authors and Affiliations

  • Yibin Wang
    • 1
  • Ning Qin
    • 1
  • Xueqiang Liu
    • 2
  1. 1.Department of Mechanical EngineeringThe University of SheffieldUK
  2. 2.Nanjing University of Aeronautics and AstronauticsChina

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