Abstract
A numerical code for supersonic intake design with a proper simulation of the normal and/or oblique shocks, boundary layer development, interaction of the shock and the boundary layer, as well as prediction of the flow separation is of great help to the designers. In this research, a numerical code is developed to solve the inner and outer flow fields of the intake and validated with various experimental tests. The intake is an axisymmetric external compression one. Roe scheme and new schemes, AUSM+-up (for all speed) and Advection Upstream Splitting Method with Pressure-Based Weight function (AUSMPW), are used to compute the convective fluxes. The original version of the AUSMPW scheme has serious problems concerning the stability and accuracy. In this investigation, several modifications are implemented to the original version of the AUSMPW scheme for the first time which resulted in a better stability and accuracy. Turbulent viscosity coefficient is computed using the Baldwin–Lomax algebraic model. The numerical results are compared well with the experimental data. It is further found that the Roe scheme has the best accuracy; however, the AUSM+-up (for all speed) scheme is numerically very efficient.
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Schedule a callMore From: Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering
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