Flow Field Analysis on the Stagnation Streamline of a Blunt Body

  • Lee, Chang-Ho (Aerodynamics Research Team, Korea Aerospace Research Institute)
  • Received : 2015.08.25
  • Accepted : 2016.05.12
  • Published : 2016.06.30


The hypersonic flow on the stagnation streamline of a blunt body is analyzed with quasi one-dimensional (1-D) Navier-Stokes equations approximated by adopting the local similarity to the two-dimensional (2-D)/axisymmetric Navier-Stokes equations. The governing equations are solved using the implicit finite volume method. The computational domain is confined from the stagnation point to the shock wave, and the shock fitting method is used to find the shock position. We propose a boundary condition at the shock, which employs the shock wave angle in the vicinity of the stagnation streamline using the shock shape correlation. As a result of numerical computation conducted for the hypersonic flow over a sphere, the proposed boundary condition is shown to improve the accuracy of the prediction of the shock standoff distance. The quasi 1-D Navier-Stokes code is efficient in computing time and is reliable for the flow analysis along the stagnation streamline and the prediction of heat flux at the stagnation point in the hypersonic blunt body flow.


Hypersonic Flow;Blunt Body;Stagnation Streamline;Heat Flux


Grant : 한국형발사체개발사업

Supported by : 한국항공우주연구원


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