Volume 30 Issue 9
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ZOU Jian-feng, SHENG Dong, FANG Lei, ZHENG Yao. Applications of anisotropic unstructured mesh adaption insupersonic combustion simulations[J]. Journal of Aerospace Power, 2015, 30(9): 2140-2150. doi: 10.13224/j.cnki.jasp.2015.09.012
Citation: ZOU Jian-feng, SHENG Dong, FANG Lei, ZHENG Yao. Applications of anisotropic unstructured mesh adaption insupersonic combustion simulations[J]. Journal of Aerospace Power, 2015, 30(9): 2140-2150. doi: 10.13224/j.cnki.jasp.2015.09.012
shu

Applications of anisotropic unstructured mesh adaption insupersonic combustion simulations

doi: 10.13224/j.cnki.jasp.2015.09.012

  • 1. School of Aeronautics and Astronautics, Zhejiang University, Hangzhou 310027, China;

  • 2. Research and Development Center, China Acedamy of Luanch Vehicle Technology, China Aerospace Science and Technology Corporation, Beijing 100076, China

  • Received Date: 2014-02-27
  • Publish Date: 2015-09-28
    Abstract
  • Anisotropic unstructured mesh adaption has been introduced and used in 2-D simulations of supersonic combustion in the DLR (Deutsches Zentrum für Luft-und Raumfahrt) scramjet combustion chamber. Three cases of non-reaction flow simulation with slip wall conditions, non-reaction flow simulation with non-slip wall conditions and reaction flow simulation (with nonslip wall conditions) were carried out. In the calculations, large gradient areas with anisotropic characteristics, such as shockwaves, jet-flows, boundary layers, and flames, were detected and well refined with anisotropic meshes. As a result, compared with the initial simulation using an isotropic mesh, element numbers were reduced by 36.2%, 36.4% and 36.8%, respectively, in case of slip conditions, nonslip conditions and reactions, meanwhile the accuracy and resolution in large gradient areas was even better. The results show high efficiency and high accuracy of anisotropic mesh approach compared with the isotropic mesh, for the problems with significant anisotropic characteristics such as supersonic combustion. It has been demonstrated that Hessian metrics based on Mach numbers can be used to generate anisotropic meshes for the supersonic combustion simulation.

     

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