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Numerical schemes having strong capability of boundary layer capture are therefore recommended for hypersonic heating prediction.
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Laminar bubble, laminar separation and boundary layer transition are quite important phenomena that must be captured by the CFD model to reproduce the actual physical aerodynamic behavior.
The boundary layer equations are (1).
The significant differences from traditional boundary layer flows are highlighted.
Boundary layer studies suggest that the velocity and temperature boundary layer thicknesses are lower for higher Reynolds numbers.
For all the grids, the mesh density in the attached boundary layer was increased to capture the transition, flow separation and most importantly the predicted separation bubble.
The rationale behind this idea is that the stall point can be accurately captured only if the boundary layer is correctly modeled.
A boundary layer flow was indirectly detected.
The boundary layer saturation is Eq. 18.
Therefore finally concentration boundary layer thickness is increases.
The diffusion boundary layer thickness was varied between 0.0025 and 0.1 cm.
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