Abstract
The laminar interaction hypersonic flowfield induced by the sweep blunt fins, which are mounted on the flat plate, is numerical studied. Finite volume method and multi-block patched meshes are used to solve three dimensional compressible Navier-Stokes equations. The influence of grid density, numerical schemes and limiter functions are studied. Spatial structure and surface flow separation pattern are descried and the influence of different sweep angles is also given. The results show that grid numbers, numerical schemes and limiter functions have huge impact on the computation results. On the basis of the computational stability, high density grid numbers, low dissipation numerical schemes and limiter functions are preferred to obtain a proper result. For the interaction flowfield, the extent of the separation region and the peak value of the heat flux are decreased as the sweep angles increase.
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Liu, Y.L., Ma, J.K. (2019). Numerical Study of Hypersonic Laminar Interaction Induced by the Swept Blunt Fins. In: Zhang, X. (eds) The Proceedings of the 2018 Asia-Pacific International Symposium on Aerospace Technology (APISAT 2018). APISAT 2018. Lecture Notes in Electrical Engineering, vol 459. Springer, Singapore. https://doi.org/10.1007/978-981-13-3305-7_36
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DOI: https://doi.org/10.1007/978-981-13-3305-7_36
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