NUMERICAL SIMULATION OF AERODYNAMIC PROBLEMS WITH STATIC MESH ADAPTATION FOR SOLUTION FEATURES
A. V. Struchkov, A. S. Kozelkov, R. N. Zhuchkov, A. A. Utkina, A. V. Sarazov
VANT. Ser.: Mat. Mod. Fiz. Proc 2019. Вып.2. С. 55-67.
The algorithm for numerical solution of aerodynamic problems based on the identification of shock-wave regions and subsequent adaptive mesh refinement in such regions is described. The method is based on the cell partitioning by adding new nodes to cell faces. The shock-wave regions, where the mesh will be refined, are identified using a pressure and density gradient criterion. The proposed algorithm is implemented on arbitrary unstructured meshes and designed for the finite-volume discretization of the system of Navier-Stokes equations. Application of the algorithm is demonstrated on the problems of transonic airflow of the NACA0012 airfoil and supersonic airflow of a wedge. The proposed adaptive mesh refinement method is shown to improve considerably the quality of the numerical solution produced on coarse meshes. Keywords: aerodynamics, numerical simulation, adaptive mesh, transonic and supersonic flow, shock waves.
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