Three dimensional laminar compressible navier stokes solver for internal rocket flow applications

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2007

Author

Coşkun, Korhan

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A three dimensional, Navier-Stokes finite volume flow solver which uses Roe’s upwind flux differencing scheme for spatial and Runge-Kutta explicit multi-stage time stepping scheme and implicit Lower-Upper Symmetric Gauss Seidel (LU-SGS) iteration scheme for temporal discretization on unstructured and hybrid meshes is developed for steady rocket internal viscous flow applications. The spatial accuracy of the solver can be selected as first or second order. Second order accuracy is achieved by piecewise linear reconstruction. Gradients of flow variables required for piecewise linear reconstruction are calculated with both Green-Gauss and Least-Squares approaches. The solver developed is first verified against the three-dimensional viscous laminar flow over flat plate. Then the implicit time stepping algorithms are compared against two rocket motor internal flow problems. Although the solver is intended for internal flows, a test case involving flow over an airfoil is also given. As the last test case, supersonic vortex flow between concentric circular arcs is selected.

Subject Keywords

Mechanical engineering., Navier-Stokes equations.

URI

http://etd.lib.metu.edu.tr/upload/12609086/index.pdf
https://hdl.handle.net/11511/17332

Collections

Graduate School of Natural and Applied Sciences, Thesis

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Citation Formats

K. Coşkun, “Three dimensional laminar compressible navier stokes solver for internal rocket flow applications,” M.S. - Master of Science, Middle East Technical University, 2007.