Improved Calculation of High Speed Inlet Flows: Part I. Numerical Algorithm

Knight, Doyle

doi:10.2514/3.50921

Cited by 23 publications

(2 citation statements)

References 29 publications

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“…The asymptotic form of the Navier-Stokes equations takes into account the diffusion terms in the direction normal to the wall only. The ability and the accuracy of this method to compute 2-D flows displaying shock/turbulent boundary layer interaction and flow separation have been successfully demonstrated in previous work by Knight [8] and [9]. In essence, it is a generalization of wall functions including pressure effects.…”

Section: Turbulent Wall-bounded Flowsmentioning

confidence: 81%

A Fully—Implicit 2‐D Navier-Stokes Algorithm for Unstructured Grids

Kergaravat

Jacon

Okong’o

et al. 1998

International Journal of Computational Fluid Dynamics

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A fully-implicit algorithm is developed for the two-dimensional, compressible, Favreaveraged Navier-Stokes equations. It incorporates the standard k -E turbulence model of Launder and Spalding and the low Reynolds number correction of Chien. The equations are solved using an unstructured grid of triangles with the flow variables stored at the centroids of the cells. A generalization of wall functions including pressure gradient effects is implemented to solve the near-wall region for turbulent flows using a separate algorithm and a hybrid grid. The inviscid fluxes are obtained from Roe's flux difference split method. Linear reconstruction of the flow variables to the cell faces provides second-order spatial accuracy. Turbulent and viscous stresses as well as heat transfer are obtained from a discrete representation of Gauss's theorem. Interpolation of the flow variables to the nodes is achieved using a second-order accurate method. Temporal discretization employs Euler, Trapezoidal or 3-Point Backward differencing. An incomplete LV factorization of the Jacobian matrix is implemented as a preconditioning method. The accuracy of the code and the efficiency of the solution strategy are presented for three test cases: a supersonic turbulent mixing layer, a supersonic laminar compression corner and a supersonic turbulent compression corner.

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Section: Turbulent Wall-bounded Flowsmentioning

confidence: 81%

A Fully—Implicit 2‐D Navier-Stokes Algorithm for Unstructured Grids

Kergaravat

Jacon

Okong’o

et al. 1998

International Journal of Computational Fluid Dynamics

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“…Knight et al 24 in their summary of canonical SWBLI studies till 2000 concluded that the RANS approach is capable of predicting the mean variables for weak to moderate SWBLIs and, however, fails to predict the strong SWBLIs as well as the unsteady nature. Similarly, several intake simulations [25][26][27][28][29][30] have shown that the wall static pressure prediction indicates some discrepancy downstream of the isolator due to the inability of turbulence models to capture the flow separation as well as the unsteadiness accurately. However, most of these studies have used Baldwin-Lomax or some variants of k-ε turbulence models.…”

Section: Introductionmentioning

confidence: 99%

Computation of viscous flow characteristics of a supersonic intake using eddy-viscosity turbulence models

Pattnaik

Rajan

2022

Proceedings of the Institution of Mechanical Engineers, Part G:

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Results of numerical investigation of flow and performance characteristics of a rectangular supersonic intake experimentally tested at Mach number of 4.03 are presented. The viscous flowfield has been obtained by solving Favre averaged Navier–Stokes equations with two eddy viscosity turbulence models, namely, Mentor’s baseline (BSL) k-ω and shear stress transport (SST) k-ω models. In addition, the effect of wall temperature conditions as well as several configurations of cowl and isolator are simulated to validate the computational methodology. The analysis has been carried out at a freestream Mach number of 4.03 and 0° angle-of-attack, corresponding to a unit Reynolds number of about 6.9×107 m−1. The predicted boundary-layer and the wall static pressure distribution using SST k-ω model shows better agreement with the experimental data compared to the BSL model and hence indicates superior capability to capture the onset and the amount of flow separation due to SWBLIs. Moreover, the terminal shock structure at different operating modes as well as the “unstart because of SWBLIs” is predicted quite accurately using the model. The wall temperature condition is found to have a strong effect on the amount of flow separation at the cowl and the subsequent interactions. Further, the results show that the sidewalls have a marginal effect on the centerline wall static pressure, though a three-dimensional flowfield with two stream-wise vortices are observed close to it as a result of the swept SWBLIs of the cowl shock with the sidewall boundary-layer leading to a higher loss in performance.

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Modelling of three-dimensional shock wave turbulent boundary layer interactions

Knight

Macroscopic Modelling of Turbulent Flows

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Improved Calculation of High Speed Inlet Flows: Part I. Numerical Algorithm

Cited by 23 publications

References 29 publications

A Fully—Implicit 2‐D Navier-Stokes Algorithm for Unstructured Grids

A Fully—Implicit 2‐D Navier-Stokes Algorithm for Unstructured Grids

Computation of viscous flow characteristics of a supersonic intake using eddy-viscosity turbulence models

Modelling of three-dimensional shock wave turbulent boundary layer interactions

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