Research on Computational Method of Supersonic Inlet/Isolator Internal Flow
نویسندگان
چکیده
In this research, a CFD solver is developed for solving the 2D/3D compressible flow problem: finite volume method based on multi-block structural grids used to solve Reynolds averaged Navier–Stokes equations (RANS). Included in methodology are multiple high-order reconstruction schemes, such as 3rd-order MUSCL (Monotone Upstreamcentered Schemes Conservation Laws), 5th-order WENO (Weight Essentially Non-Oscillatory), and MP (Monotonicity-Preserving) schemes. Of variety of turbulence models that embedded, mainly shear stress transport model (SST), which compatible with OpenMP/MPI parallel algorithms. This research uses conduct steady-state simulation two-dimensional supersonic inlet/isolator, incorporating these high-precision schemes accurately capture shock wave/expansion wave interaction wave/turbulent boundary layer (SWTBLI), among other effects. By comparing computation results same inlet configuration, it found 3D effects side wall cannot be ignored due existing strong lateral near corner. To obtain more refined simulation, commercial software ANSYS Fluent 18.0 carry out detached eddy (DES) large (LES) inlet, so reveal details separation area layers.
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ژورنال
عنوان ژورنال: Applied sciences
سال: 2021
ISSN: ['2076-3417']
DOI: https://doi.org/10.3390/app11199272