Numerical simulation of the interaction of a shock wave with a supersonic laminar boundary layer in the presence of heat and mass exchange with the surface
DOI:
https://doi.org/10.34185/1562-9945-5-160-2025-08Keywords:
numerical simulation, shock wave, laminar boundary layer, heat and mass transferAbstract
The results of parametric numerical experiments on the influence of heat and mass transfer on flow separation during the interaction of an oblique shock wave with a laminar boundary layer are presented. An implicit finite-volume algorithm for solving the Navier-Stokes equations for arbitrary coordinates, based on the Roe scheme for convective terms, is implemented. The second order of accuracy in space was provided by using the symmetric Jamecon flux limiter. The numerical algorithm was verified on the problems of transonic and supersonic laminar and turbulent flows when compared with experimental data.
The study was carried out with the aim of comparative analysis of the possibilities of the flow separation control using heat and mass transfer with a streamlined surface under the same conditions of the shock wave/boundary layer interaction.
Spatial pressure distributions, pressure and skin friction coefficient distributions along the plate, profiles of density, dynamic viscosity coefficient, longitudinal velocity components and momentum in the laminar boundary layer are presented. The main physical factors de-termining changes in the structure of the separation interaction under heat and mass transfer conditions were identified. The effect of heat transfer with the plate was manifested primarily in changes in the profiles of density and dynamic viscosity coefficient, which significantly de-pend on temperature. Removal of slowed particles from the boundary layer leads to a greater filling of the velocity profile by mass transfer with the practically constant value of the dy-namic viscosity coefficient on the surface.
Based on the analysis of the results obtained, it was found that the main factor in pre-venting flow separation is the increase in the longitudinal component of the momentum dur-ing plate cooling by heat transfer and the removal of slowed particles by mass transfer. Therefore, despite the different physical nature of the impact, heat and mass transfer with the surface has a similar resulting effect on the size and structure of the supersonic separation zone.
Using heat and mass transfer it is possible to prevent the occurrence of a separation zone in two-dimensional supersonic flows.
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