Abstract
Laminar hypersonic flows over the nose of a spacecraft and an ellipsoid at angle of attack are simulated by a semi-implicit finite-difference method. The central discretization of the thin-layer Navier-Stokes equations is explicit in the surface tangential directions and implicit in the normal direction. The scheme operates as a checkerboard line relaxation method, and requires only the conservative variables and the Cartesian coordinates to be permanently stored. The code is verified by comparison with axisymmetric computational results and with experiments. Attached flow is predicted for the spacecraft nose, and separated flow is observed for the ellipsoid.
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References
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© 1989 Springer-Verlag
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Riedelbauch, S., Müller, B., Kordulla, W. (1989). Semi-implicit finite-difference simulation of laminar hypersonic flow over blunt bodies. In: Dwoyer, D.L., Hussaini, M.Y., Voigt, R.G. (eds) 11th International Conference on Numerical Methods in Fluid Dynamics. Lecture Notes in Physics, vol 323. Springer, Berlin, Heidelberg. https://doi.org/10.1007/3-540-51048-6_81
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DOI: https://doi.org/10.1007/3-540-51048-6_81
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