Shock wave/boundary layer interaction(SWBLI)continues to pose a significant chal-lenge in the field of aerospace *** paper aims to address this issue by proposing a novel approach for predicting aerodynamic coefficien...
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Shock wave/boundary layer interaction(SWBLI)continues to pose a significant chal-lenge in the field of aerospace *** paper aims to address this issue by proposing a novel approach for predicting aerodynamic coefficients and heat trans-fer in viscous supersonic and hypersonic flows using a high-order flux reconstruction ***,finite volume methods are extensively employed for the compu-tation of skin aerodynamic coefficients and heat ***,these numerical methods exhibit considerable susceptibility to a range of factors,including the inviscid flux function and the computational *** application of high-order flux recon-struction techniques offers promising potential in alleviating these *** contrast to other high-order methods,the flux reconstruction is combined with the lat-tice Boltzmann flux solver in this *** current method evaluates the common inviscid flux at the cell interface by locally reconstructing the lattice Boltzmann equa-tion solution from macroscopic flow variables at solution ***,this framework performs a positivity-preserving,entropy-based adaptive filtering method for shock *** present approach is validated by simulating the double Mach reflection,and then simulating some typical viscous *** results demonstrate that the current method accurately predicts aerodynamic coefficients and heat trans-fer,providing valuable insights into the application of high-order methods for shock wave/boundary layer interaction.
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