NASA Technical Reports Server (NTRS) : Implicit pdf

NASA Technical Reports Server (NTRS) : Implicit

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Numerical investigation of flow separation over a NACA 0012 airfoil at large angles of attack has been carried out. The numerical calculation is performed by solving the full Navier-Stokes equations in generalized curvilinear coordinates. The second-order LU-SGS implicit scheme is applied for time integration. This scheme requires no tridiagonal inversion and is capable of being completely vectorized, provided the corresponding Jacobian matrices are properly selected. A fourth-order centered compact scheme is used for spatial derivatives. In order to reduce numerical oscillation, a sixth-order implicit filter is employed. Non-reflecting boundary conditions are imposed at the far-field and outlet boundaries to avoid possible non-physical wave reflection. Complex flow separation and vortex shedding phenomenon have been observed and discussed

• Creator/s: NASA Technical Reports Server (NTRS
• Date: 1/1/1999
• Year: 1999
• Book Topics/Themes: NASA Technical Reports Server (NTRS), MULTIGRID METHODS, CONVERGENCE, DIRECT NUMERICAL SIMULATION, BOUNDARY LAYER SEPARATION, COMPUTATIONAL FLUID DYNAMICS, AIRFOILS, ANGLE OF ATTACK, NAVIER-STOKES EQUATION, JACOBI MATRIX METHOD, DERIVATION, OSCILLATIONS, VORTEX SHEDDING, GRID GENERATION (MATHEMATICS), Liu, Chao-Qun, Shan, H., Jiang, L

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