Numerical simulation of aerodynamic problems based on adaptive mesh refinement method

Numerical simulation of aerodynamic problems using an algorithm, which identifies shock regions and refines the mesh there using an adaptive mesh refinement method, is performed. The static mesh adaptation method is based on cell partitioning by adding new nodes to cell faces. The method of identifi...

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Bibliographic Details
Published in:	Acta astronautica Vol. 172; pp. 7 - 15
Main Authors:	Struchkov, A.V., Kozelkov, A.S., Volkov, K.N., Kurkin, A.A., Zhuckov, R.N., Sarazov, A.V.
Format:	Journal Article
Language:	English
Published:	Elmsford Elsevier Ltd 01-07-2020 Elsevier BV
Subjects:	Adaptation Adaptive mesh Aerodynamics Algorithms Computation Computational fluid dynamics Computer simulation Density gradients Drag coefficients Finite element method Flight safety Gas jets Grid refinement (mathematics) High-speed flow Hypersonic flow Mathematical analysis Mesh generation Nose cones Numerical simulations Shock wave Shock waves Wind tunnels Adaptive mesh Aerodynamics Flight safety Computational fluid dynamics Shock wave High-speed flow
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Summary:	Numerical simulation of aerodynamic problems using an algorithm, which identifies shock regions and refines the mesh there using an adaptive mesh refinement method, is performed. The static mesh adaptation method is based on cell partitioning by adding new nodes to cell faces. The method of identification of the shock regions using a pressure and density gradient criterion and its verification are presented. The use and applications of the developed algorithm are illustrated, and supersonic and hypersonic flows with strong shock waves are calculated. The results computed explore the shock-wave structure of the flow, which develops near the nose cone section of a body and determines its aerodynamic performance. The aerodynamic performance of bodies with different nose cone designs, including a body with a spike and a pointed cone with an opposing gas jet injected from the nose section, are evaluated based on the proposed method. The method of static mesh adaptation provides a visually sharper picture of the flow around the body and reduces the numerical error of drag coefficient calculations in comparison with wind tunnel measurements. The results computed on meshes of similar resolution constructed with the adaptation method and automatic mesh generator are compared. The results computed on the adaptive mesh are similar to those computed on the mesh generated automatically, but the adaptive mesh has a smaller number of cells. •Adaptive mesh refinement method is developed.•Problems related to high-speed compressible flow are considered.•The results computed are compared with those from other methods.
ISSN:	0094-5765 1879-2030
DOI:	10.1016/j.actaastro.2020.03.019