Improved Numerical Simulations of Incompressible Flows Based on Viscous/Inviscid Interaction Procedures

Hafez, Mohammed M.; Shatalov, A.; Nakajima, Masahiro

doi:10.1007/978-3-540-92779-2_47

Cited by 4 publications

(5 citation statements)

References 5 publications

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“…[13] and [49] at Re 500 and 10 which shows well agreement. The time evolution of the drag and lift coefficients of the NACA0012 wing section are shown in Fig.…”

Section: Flow Around a Naca0012 Wing Sectionsupporting

confidence: 52%

Implementation of a curved wall- and an absorbing open-boundary condition for the D3Q19 lattice Boltzmann method for simulation of incompressible fluid flows

Ezzatneshan

2018

Scientia Iranica

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“…[13] and [49] at Re 500 and 10 which shows well agreement. The time evolution of the drag and lift coefficients of the NACA0012 wing section are shown in Fig.…”

Section: Flow Around a Naca0012 Wing Sectionsupporting

confidence: 52%

Implementation of a curved wall- and an absorbing open-boundary condition for the D3Q19 lattice Boltzmann method for simulation of incompressible fluid flows

Ezzatneshan

2018

Scientia Iranica

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“…Comparison of u ‐velocity contours with that of Hafez et al , Re = 500, AOA = 10°. Mod.AVR, modified averaging; ROE, Roe; OCB, original characteristic‐based; RCB, revised characteristic‐based.…”

Section: Numerical Results and Discussionmentioning

confidence: 94%

“…Hafez et al [10] numerically obtained steady solution at Re D 500 and AOA D 10 ı . They modeled flow by finite-volume method using Helmholtz-type velocity decomposition.…”

Section: Introductionmentioning

confidence: 99%

“…It is shown that CB schemes resulted in a faster convergence that demonstrates their capability to handle incompressible flows. The wall pressure and skin friction distributions for Re D 500, AOA D 10 ı , are compared to those of Hafez et al [10] in Figures 7 and 8, respectively. The horizontal velocity components at Re D 2000, AOA D 0 ı , at 20% and 80% of the chord are plotted in Figures 9 and 10, respectively.…”

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confidence: 99%

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A comparative investigation of hydrofoil at angles of attack

Razavi

Orang

2011

Numerical Methods in Fluids

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SUMMARYIn this paper, a numerical investigation of incompressible flow around a hydrofoil is presented. The laminar flow was modeled at different angles of attack. Momentum and continuity equations were coupled by the artificial compressibility scheme. In finite-volume method, convective fluxes were calculated and compared by four schemes. Flux averaging with pressure correction was used. The other characteristic-based (CB) methods consisted of Roe scheme and original CB scheme. A revised CB scheme was implemented in this research, which demonstrated very accurate solutions with respect to others. The results confirmed the superiority of the revised upwind scheme regarding accuracy and convergence without any requirement to artificial viscosity. The problem was studied at high Reynolds numbers at the onset of turbulence. For time discretization, the fifth-order Runge-Kutta scheme was used. Results were compared with those of others in which good agreement was observed. Numerical experiments were performed on the NACA0012 hydrofoil.

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“…Although present study has focused on the aeroheating literature, it is noted that viscous-inviscid solution procedure has been applied to other regimes of flow, as well [18][19][20][21]. In these works, effect of boundary-layer displacement on the surface pressure distribution, and in return, again on the viscous flow has been studied for aerofoils.…”

Section: Introductionmentioning

confidence: 99%

Calculation of the viscous-interaction effects in the Euler/boundary-layer methods

Parhizkar

Karimian

2008

Proceedings of the Institution of Mechanical Engineers, Part G:

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A simple approach is proposed to incorporate the effect of viscous interaction in the calculation of aerodynamic heating of three-dimensional geometries by Euler/boundary-layer methods. In the present study, aerodynamic heating is calculated from the solution of a set of approximate convective-heating equations along the streamlines. These heating equations are derived using axisymmetric analogue. To determine streamline paths and flow properties along them, Euler equations are solved around the three-dimensional body. The effect of viscous interaction on the aerodynamic heating can be significant, especially if the Reynolds number is low. To incorporate this effect, the whole process should be repeated having considered the boundarylayer thickness all around the body. However, this approach causes different difficulties, and is not cost efficient as well. In the present work, the effect of boundary-layer thickness on the aerodynamic heating is incorporated through the correction of pressure distribution on the surface of the body. This approach of correcting pressure distribution is applied to spherical and elliptical blunted cones in laminar hypersonic flows. It is shown that the heating rates are improved in low Reynolds numbers, where viscous-interaction effect is significant. The present approach can result in a reduction of computational cost, when viscous interaction is significant in calculation of aerodynamic heating.

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Improved Numerical Simulations of Incompressible Flows Based on Viscous/Inviscid Interaction Procedures

Cited by 4 publications

References 5 publications

Implementation of a curved wall- and an absorbing open-boundary condition for the D3Q19 lattice Boltzmann method for simulation of incompressible fluid flows

Implementation of a curved wall- and an absorbing open-boundary condition for the D3Q19 lattice Boltzmann method for simulation of incompressible fluid flows

A comparative investigation of hydrofoil at angles of attack

Calculation of the viscous-interaction effects in the Euler/boundary-layer methods

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