Turbulence characteristics of supersonic boundary layer past a backward facing step

Arai, T.; Sugiyama, Hiromu; Homareda, Manabu; Uno, Naotsugu

doi:10.2514/6.1995-6126

Cited by 9 publications

(8 citation statements)

References 5 publications

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“…McDonald [1] and Rom [2] applied the momentum integral method to obtain the base pressure, where flow conditions in the reattachment zone were explicitly described. Recently, nonintrusive optical methods such as laser Doppler velocimetry (LDV) [3][4][5] and planar laserinduced fluorescence (PLIF) [6] have been applied to measure the flow properties directly. A number of computational fluid dynamics (CFD) researchers solved Euler [7,8] and Navier-Stokes [5,[9][10][11][12][13] equations to investigate the supersonic flows over a backward-facing step.…”

Section: Introductionmentioning

confidence: 99%

“…Recently, nonintrusive optical methods such as laser Doppler velocimetry (LDV) [3][4][5] and planar laserinduced fluorescence (PLIF) [6] have been applied to measure the flow properties directly. A number of computational fluid dynamics (CFD) researchers solved Euler [7,8] and Navier-Stokes [5,[9][10][11][12][13] equations to investigate the supersonic flows over a backward-facing step. Loth et al [7] utilized the finite-element method-flux corrected transport algorithm and adaptive unstructured gridding to solve the unsteady Euler equations.…”

Section: Introductionmentioning

confidence: 99%

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Remeshing Strategy of the Supersonic Turbulent Flow Over a Backward-Facing Step

Yang¹

2004

Numerical Heat Transfer, Part B: Fundamentals

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A modified error indicator and a locally implicit scheme with anisotropic dissipation model on quadrilateral-triangular mesh are developed to study the supersonic turbulent flow over a backward-facing step. In the Cartesian coordinate system, the unsteady Favre-averaged Navier-Stokes equations with a low-Reynolds-number k-« turbulence model are solved. The modified error indicator, in which the unified magnitude of substantial derivative of pressure and unified magnitude of substantial derivative of vorticity magnitude are incorporated, is applied to treat the new node spacing of mesh remeshing. To assess the present approach, the transsonic turbulent flow around an NACA 0012 airfoil is performed. According to the high-resolution result on the adaptive mesh, the structure of the back-step corner vortex, expansion wave, and oblique shock wave are distinctly captured.

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Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Remeshing Strategy of the Supersonic Turbulent Flow Over a Backward-Facing Step

Yang¹

2004

Numerical Heat Transfer, Part B: Fundamentals

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“…The mesh reÿnement with a two-level reÿnement procedure was employed. Arai et al [5] applied the total variation diminishing (TVD) ÿnite-di erence scheme, in which eddy viscosity was determined using Baldwin-Lomax turbulence model. Kuruvila and Anderson [9] solved the Navier-Stokes equations by means of MacCormack scheme with a fourth-order numerical dissipation term.…”

Section: Introductionmentioning

confidence: 99%

“…McDonald [1] and Rom [2] applied the momentum integral method to obtain the base pressure, where ow conditions in the reattachment zone were explicitly described. Recently, non-intrusive optical methods such as the laser Doppler velocimetry (LDV) [3][4][5] and planar laser-induced uorescence (PLIF) [6] have been applied to measure the ow properties directly. A number of CFD researchers solved Euler [7,8] and Navier-Stokes [5,[9][10][11][12][13] equations to investigate the supersonic ows over a backward-facing step.…”

Section: Introductionmentioning

confidence: 99%

“…Recently, non-intrusive optical methods such as the laser Doppler velocimetry (LDV) [3][4][5] and planar laser-induced uorescence (PLIF) [6] have been applied to measure the ow properties directly. A number of CFD researchers solved Euler [7,8] and Navier-Stokes [5,[9][10][11][12][13] equations to investigate the supersonic ows over a backward-facing step. Loth et al [7] utilized the ÿnite element method-ux corrected transport algorithm and adaptive unstructured gridding to solve the unsteady Euler equations.…”

Section: Introductionmentioning

confidence: 99%

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Adaptive strategy of the supersonic turbulent flow over a backward‐facing step

Yang

2004

Numerical Methods in Fluids

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SUMMARYAn adaptive strategy incorporating mesh remeshing and reÿning is developed to study the supersonic turbulent ow over a backward-facing step on a mixed quadrilateral-triangular mesh. In the Cartesian co-ordinate system, the unsteady Favre-averaged Navier-Stokes equations with a low-Reynolds-number k-turbulence model are solved using a locally implicit scheme with an anisotropic dissipation model. In the present adaptive strategy, two error indicators for both mesh remeshing and reÿning, respectively, are presented. The remeshing error indicator incorporates uniÿed magnitude of substantial derivative of pressure and that of vorticity magnitude, whereas the reÿning error indicator incorporates uniÿed magnitude of substantial derivative of pressure and that of weighted vorticity magnitude. To assess the present approach, the transonic turbulent ow around an NACA 0012 airfoil is performed. Based on the comparison with the experimental data, the accuracy of the present approach is conÿrmed. According to the high-resolutional result on the adaptive mesh, the structure of backstep corner vortex, expansion wave and oblique shock wave is distinctly captured.

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Numerical solution of the turbulent supersonic flow over a backward facing step

Halupovich¹,

Natan²,

Rom³

1999

Fluid Dyn. Res.

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The steady two-dimensional viscous supersonic turbulent ow over a backward facing step was calculated using the PHOENICS CFD code. The two-equation k-turbulence model was employed for the turbulent ow simulation. The e ects of the incoming boundary layer, Reynolds number and inlet Mach number on the ow were investigated. The maximum free stream Mach number was 3.5. The PHOENICS code was found to be adequate for supersonic ow simulations with M 63:5, however, at hypersonic turbulent ow conditions convergence was not obtained. The numerical results indicate that the separation point is positioned on the step face, below the corner. The calculations also show that a lip shock is formed to match the ow conditions at the step corner. The results exhibit favorable agreement with data from both experiments and other numerical simulations.

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Turbulence characteristics of supersonic boundary layer past a backward facing step

Cited by 9 publications

References 5 publications

Remeshing Strategy of the Supersonic Turbulent Flow Over a Backward-Facing Step

Remeshing Strategy of the Supersonic Turbulent Flow Over a Backward-Facing Step

Adaptive strategy of the supersonic turbulent flow over a backward‐facing step

Numerical solution of the turbulent supersonic flow over a backward facing step

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