A numerical analysis of supersonic flow over an axisymmetric afterbody

Tucker, P. Kevin; Shyy, Wei

doi:10.2514/6.1993-2347

Cited by 42 publications

(26 citation statements)

References 14 publications

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“…Both studies addressed the effectiveness of turbulence models in representing adequately the evolution of the flow field. In the study of Tucker and Shyy [12], an extension to the k-e-based modeling approach (referred to here as Eke) gave a better accounting of the flow field development than the unmodified model (Ske), which was in sharp contrast to the results that were seen in our calculations [11]. The particular form of the models of turbulence are not relevant for this study.…”

Section: Treatment Of Convective Fluxescontrasting

confidence: 69%

“…In a prior study of the axisymmetric afterbody flow field [11], results obtained with the artificial dissipation scheme-based approach (of computing the inviscid fluxes) were not consistent with previously published results of the same flow field [12]. Both studies addressed the effectiveness of turbulence models in representing adequately the evolution of the flow field.…”

Section: Treatment Of Convective Fluxesmentioning

confidence: 65%

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Treatment of Iimviscid Fluxes in Compressible Turbulent Flow Computations

Krishnamurty

Shyy

1998

Numerical Heat Transfer, Part B: Fundamentals

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Section: Treatment Of Convective Fluxescontrasting

confidence: 69%

Section: Treatment Of Convective Fluxesmentioning

confidence: 65%

Treatment of Iimviscid Fluxes in Compressible Turbulent Flow Computations

Krishnamurty

Shyy

1998

Numerical Heat Transfer, Part B: Fundamentals

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“…Sarkar (1992) introduced a simplified model, that algebraically relates the pressure-dilatation to quantities 36 obtained in incompressible closures. Tucker & Shyy (1993) and, more recently, Krishnamurty & Shyy (1997) made an assessment of K − ε model RANS calculations of the UIUC flow using the full NavierStokes equations. They incorporated the above mentioned as well as additional compressibility extensions and showed some improvement over previous results.…”

Section: Turbulence Modellingmentioning

confidence: 99%

“…They incorporated the above mentioned as well as additional compressibility extensions and showed some improvement over previous results. However, Tucker & Shyy (1993) found that the eddy viscosity in the recirculation region and the K-level in the shear layer were overpredicted and mentioned that the model did not account for baroclinic torque, which is an important factor in the TKE budget.…”

Section: Turbulence Modellingmentioning

confidence: 99%

Simulation of Supersonic Base Flows: Numerical Investigations Using DNS, LES, and URANS

Fasel¹,

Sandberg²

2006

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Public Reporting Burden for this collection of information is estimated to average 1 hour per response, including the time for reviewing instructions, searching existing data sources, gathering and maintaining the data needed, and completing and reviewing the collection of information. Send comment regarding this burden estimate or any other aspect of this collection of information, including suggesstions for reducing this burden, Simulation of Supersonic Base Flows: Numerical Investigations Using DNS, LES, and URANS Report Title ABSTRACTTransitional and turbulent supersonic axisymmetric wakes were investigated by conducting various numerical experiments. The main objective was to identify hydrodynamic instability mechanisms in the flow at Mach number M = 2.46 for several Reynolds numbers, and relating these to coherent structures that are found from various visualization techniques. The premise for this approach is the assumption that flow instabilities lead to the formation of coherent structures. The effect of these structures on the mean flow is of particular interest, as they strongly affect the base drag. Three high-order accurate compressible codes were developed in cylindrical coordinates for this research: A spatial Navier-Stokes (N-S) code to conduct Direct Numerical Simulations (DNS), a linearized N-S code for linear stability investigations using two-dimensional basic states, and a temporal N-S code for performing local stability analyses. The ability of numerical simulations to deliberately exclude physical effects is exploited. This includes intentionally eliminating certain azimuthal/helical modes by employing DNS for various circumferential domain-sizes. With this approach, the impact of structures associated with certain modes on the global wake-behavior can be scrutinized. It is concluded that azimuthal modes with low wavenumbers are responsible for a flat mean base-pressure distribution and that k=2 and k=4 are the dominant modes in the trailing wake, producing a four-lobe wake pattern. Complementary spatial and temporal calculations are carried out to investigate whether instabilities are of local or global nature. Circumstatial evidence is presented that absolutely unstable global modes within the recirculation region coexist with convectively unstable shear-layer modes. The flow is found to be absolutely unstable with respect to modes k>0 for Re_D > 5,000 and with respect to the axisymmetric mode for Re_D>100,000. Furthermore, it is investigated whether flow control measures designed to weaken the naturally most significant modes can decrease the base drag. Finally, the novel Flow Simulation Methodology (FSM), using state-of-the-art turbulence closures, was shown to reproduce DNS results at a fraction of the computational cost.

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“…Yang et al [11] employed a ux-vector splitting lower-upper symmetric successive overrelaxation scheme, and deduced that reduction of the base pressure and recirculation zone could cause di culties in ignition and ameholding in Scramjet combustors. Tucker and Shyy [12] introduced the FDNS code [14], in which k-turbulence model was corrected to treat compressible ows. Halupovich et al [13] utilized the PHOENICS code and k-turbulence model to investigate the supersonic backstep ow.…”

Section: Introductionmentioning

confidence: 99%

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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A numerical analysis of supersonic flow over an axisymmetric afterbody

Cited by 42 publications

References 14 publications

Treatment of Iimviscid Fluxes in Compressible Turbulent Flow Computations

Treatment of Iimviscid Fluxes in Compressible Turbulent Flow Computations

Simulation of Supersonic Base Flows: Numerical Investigations Using DNS, LES, and URANS

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

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