Flow Topology and Secondary Separation Modelling at Crossing Shock Wave/Turbulent Boundary Layer Interaction Conditions

Salin, Andrea; Yao, Yufeng; Zheltovodov, A. A.

doi:10.1260/1757-2258.4.1-2.13

Cited by 2 publications

(7 citation statements)

References 21 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…In addition, two new saddle points C 2 and C 2 1 are captured slightly ahead of a central node point N 1 . For any further details on flow topology and structure analysis predicted by different turbulence models please consult the work carried out by Salin et al [13]. In the present work, it is important highlighting that an improvement of surface flow pattern obtained by the RSM model indeed reflects to an improved wall pressure and HTC numerical predictions.…”

Section: Methodsmentioning

confidence: 69%

“…All models studied over-predicted the wall heat transfer coefficient although the RSM turbulence model better agrees with the experiment only along the TML. This ability of reproducing the secondary separation phenomenon observed in the experiment [1,2] and recent numerical study [13] does not improve the numerical disagreement of C h , particularly along the spanwise direction. The near-wall turbulence intensity of RSM is in fact two-order of magnitude lower than that of the SST model.…”

Section: B Comparison and Improvement Of Htc Predictionsmentioning

confidence: 87%

“…The inviscid shock relations in terms of pressure jump at TML and cross-sections I and II are also plotted on the same figures for reference. Grid refinement studies were carried out and results have been reported in references [12,13]. Here, only findings from fine and very fine grids (see respectively DF4-7 and DF4-15 in Table 1) are presented and normalized wall pressure (P/P 1 , where P 1 denotes the undisturbed free-stream wall pressure) variations are validated against test data.…”

Section: Methodsmentioning

confidence: 99%

“…aspect ratio, skewness). Further details can be found in Salin et al [13]. Results obtained from fine and very fine grids are presented in this work for the DF4-7 and DF4-15 configurations, respectively.…”

Section: Experimental Conditions and Numerical Treatmentsmentioning

confidence: 96%

See 3 more Smart Citations

Comparison and Improvement of Wall Heat Transfer Prediction in Crossing-Shock-Wave/Turbulent-Boundary-Layer Interaction Conditions

Salin¹,

Yao²,

Zheltovodov

et al. 2013

51st AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

Self Cite

View full text Add to dashboard Cite

Numerical study has been carried out for a symmetrical double-sharp-fin configuration with inclination angles 7° and 15°, Mach 3.92 and Reynolds number Re  = 3.08×10 5 , aiming for comparison and improvement wall heat transfer predictions at weak and medium/strong interaction conditions. Turbulence model influences using the ω-based Reynolds Stress model (RSM), two-equation Shear Stress Transport (SST), and one-equation Eddy Viscosity Transport (EVT) were studied, and wall heat transfer coefficients (HTC) were evaluated by two formulations, corresponding to previous experimental and numerical studies. It was found that compared to experiments, steady RANS computation using eddy-viscosity models SST and EVT over-predicts HTC by max 50%, due to the over-prediction of wall heat flux q w which is a critical parameter in determining wall HTC. Some improvements were obtained by using RANS-RSM modeling which improved the prediction by 50%, but still over-predict wall HTC by max 25% compared to test. To further improve HTC prediction, three methods of calculating q w were attempted and resultant wall HTC was compared with experimental measurements. It was found that by artificially increasing the near-wall turbulent Prandtl number by a factor of 10, RANS predicted lateral wall HTC is in good agreement with available test data. A pressure-correlation based approach is also able to produce much better wall HTC prediction, in good agreement with test data for moderate/strong interaction conditions. Further comparisons were made on surface flow topology and it was found that RANS modeling was in good qualitatively agreement with experimental oil-flow visualization, and in particular RANS-RSM is able to reproduce the secondary separation phenomenon observed in experiment, due to its ability to evaluate correct level of turbulence kinetic energy that is critical in determining pseudo-laminar state of an embedded reversed flow underneath the main cross-flow vortex. 2 HTC = heat transfer coefficient I, II, III = cross sections on the flat plate L = length of the fin M = Mach number N = number of grid points P = pressure Pr t = turbulent Prandtl number q w = wall heat transfer R = reattachment (divergence) line Re = Reynolds number RSM = Reynolds Stress Model S = separation (convergence) line SST = Shear Stress Transport T = temperature TML = centerline or throat middle line on the flat plate U = magnitude of the velocity x, y, z = coordinates along the free-stream, wall-normal, and span-wise directions, respectively δ = boundary layer thickness θ = boundary layer momentum thickness λ = thermal conductivity μ = dynamic viscosity ρ = density τ = shear stress Subscripts ∞ = free-stream condition 0 = condition where free-stream flow is measured 1 = flow conditions at x=30 mm of an undisturbed flat-plate boundary layer a = adiabatic wall condition f = fluid r = recovery factor t = turbulent w = wall Superscripts 0 = total 1 = symmetric counterpart + = non-dimensional

show abstract

Section: Methodsmentioning

confidence: 69%

Section: B Comparison and Improvement Of Htc Predictionsmentioning

confidence: 87%

Section: Methodsmentioning

confidence: 99%

Section: Experimental Conditions and Numerical Treatmentsmentioning

confidence: 96%

See 2 more Smart Citations

Comparison and Improvement of Wall Heat Transfer Prediction in Crossing-Shock-Wave/Turbulent-Boundary-Layer Interaction Conditions

Salin¹,

Yao²,

Zheltovodov

et al. 2013

51st AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

Self Cite

View full text Add to dashboard Cite

show abstract

“…The flow configuration and its computational domain are sketched in Figure 1. The computational domain in the present study only contains the compression side of the fin, where the 3D SWTBLI happens, and the other side of the fin is discarded to simplify the simulation, consistent with other numerical simulations found in literature [40][41][42] . The The mesh was generated based on the criterion proposed by Sagaut [43] for LES of boundary layer flows, known as ∆!…”

Section: B Computational Domain and Meshmentioning

confidence: 65%

Investigation of Three-Dimensional Shock Wave/Turbulent-Boundary-Layer Interaction Initiated by a Single Fin

et al. 2017

Self Cite

View full text Add to dashboard Cite

Investigation of three-dimensional shock wave/turbulent-boundary-layer interaction initiated by a single fin. AIAA Journal, 55 (2). pp. 509-523. ISSN 0001-1452 Available from: http://eprints.uwe.ac.uk/30142We recommend you cite the published version. The publisher's URL is: http://dx.doi.org/10.2514/1.J055283 Refereed: YesCopyright c 2016 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved. Disclaimer UWE has obtained warranties from all depositors as to their title in the material deposited and as to their right to deposit such material. UWE makes no representation or warranties of commercial utility, title, or fitness for a particular purpose or any other warranty, express or implied in respect of any material deposited. UWE makes no representation that the use of the materials will not infringe any patent, copyright, trademark or other property or proprietary rights. UWE accepts no liability for any infringement of intellectual property rights in any material deposited but will remove such material from public view pending investigation in the event of an allegation of any such infringement. PLEASE SCROLL DOWN FOR TEXT.

show abstract

Flow Topology and Secondary Separation Modelling at Crossing Shock Wave/Turbulent Boundary Layer Interaction Conditions

Cited by 2 publications

References 21 publications

Comparison and Improvement of Wall Heat Transfer Prediction in Crossing-Shock-Wave/Turbulent-Boundary-Layer Interaction Conditions

Comparison and Improvement of Wall Heat Transfer Prediction in Crossing-Shock-Wave/Turbulent-Boundary-Layer Interaction Conditions

Investigation of Three-Dimensional Shock Wave/Turbulent-Boundary-Layer Interaction Initiated by a Single Fin

Contact Info

Product

Resources

About