Numerical simulation of aerodynamic problems based on adaptive mesh refinement method

摘要: Abstract Numerical simulation of aerodynamic problems using an algorithm, which identifies shock regions and refines the mesh there adaptive refinement method, is performed. The static adaptation method based on cell partitioning by adding new nodes to faces. identification a pressure density gradient criterion its verification are presented. use applications developed algorithm illustrated, supersonic hypersonic flows with strong waves calculated. results computed explore shock-wave structure flow, develops near nose cone section body determines performance. performance bodies different designs, including spike pointed opposing gas jet injected from section, evaluated proposed method. provides visually sharper picture flow around reduces numerical error drag coefficient calculations in comparison wind tunnel measurements. meshes similar resolution constructed automatic generator compared. those generated automatically, but has smaller number cells.