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  • 1
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    Development of DDES and IDDES Formulations for the k-ω Shear Stress Transport Model (2011)
    Springer
    Details
    Publication Date: 2011-11-22
    Print ISSN: 1386-6184
    Electronic ISSN: 1573-1987
    Topics: Mechanical Engineering, Materials Science, Production Engineering, Mining and Metallurgy, Traffic Engineering, Precision Mechanics
    Published by Springer
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    PAPER CURRENT
  • 2
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    A One-Equation Local Correlation-Based Transition Model (2015)
    Springer
    Details
    Publication Date: 2015-07-05
    Print ISSN: 1386-6184
    Electronic ISSN: 1573-1987
    Topics: Mechanical Engineering, Materials Science, Production Engineering, Mining and Metallurgy, Traffic Engineering, Precision Mechanics
    Published by Springer
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  • 3
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    An Overview of Hybrid RANS–LES Models Developed for Industrial CFD (2021)
    Molecular Diversity Preservation International
    Details
    Publication Date: 2021-03-10
    Description: An overview of scale-resolving simulation (SRS) methods used in ANSYS Computational Fluid Dynamics (CFD) software is provided. The main challenges, especially when computing boundary layers in large eddy simulation (LES) mode, will be discussed. The different strategies for handling wall-bound flows using combinations of RANS and LES models will be explained, along with some specific application examples. It will be demonstrated that the stress-blended eddy simulation (SBES) approach is optimal for applications with a mix of boundary layers and free shear flows due to its low cost and its ability to handle boundary layers in both RANS and wall-modeled LES (WMLES) modes.
    Electronic ISSN: 2076-3417
    Topics: Natural Sciences in General
    Published by Molecular Diversity Preservation International
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  • 4
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    Boundary-layer transition and global skin friction measurement with an oil-fringe imaging technique (1993)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A new oil-fringe imaging system skin friction (FISF) technique to measure skin friction on wind tunnel models is presented. In the method used to demonstrate the technique, lines of oil are applied on surfaces that connect the intended sets of measurement points, and then a wind tunnel is run so that the oil thins and forms interference fringes that are spaced in proportion to local skin friction. After a run the fringe spacings are imaged with a CCD-array digital camera and measured on a computer. Skin friction and transition measurements on a two-dimensional wing are presented and compared with computational predictions.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-CR-198814 , NAS 1.26:198814
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Assessment of higher order turbulence models for complex two- and three-dimensional flowfields (1992)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A numerical method is presented to solve the three-dimensional Navier-Stokes equations in combination with a full Reynolds-stress turbulence model. Computations will be shown for three complex flowfields. The results of the Reynolds-stress model will be compared with those predicted by two different versions of the k-omega model. It will be shown that an improved version of the k-omega model gives as accurate results as the Reynolds-stress model.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-TM-103944 , A-92124 , NAS 1.15:103944
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Improved two-equation k-omega turbulence models for aerodynamic flows (1992)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Two new versions of the k-omega two-equation turbulence model will be presented. The new Baseline (BSL) model is designed to give results similar to those of the original k-omega model of Wilcox, but without its strong dependency on arbitrary freestream values. The BSL model is identical to the Wilcox model in the inner 50 percent of the boundary-layer but changes gradually to the high Reynolds number Jones-Launder k-epsilon model (in a k-omega formulation) towards the boundary-layer edge. The new model is also virtually identical to the Jones-Lauder model for free shear layers. The second version of the model is called Shear-Stress Transport (SST) model. It is based on the BSL model, but has the additional ability to account for the transport of the principal shear stress in adverse pressure gradient boundary-layers. The model is based on Bradshaw's assumption that the principal shear stress is proportional to the turbulent kinetic energy, which is introduced into the definition of the eddy-viscosity. Both models are tested for a large number of different flowfields. The results of the BSL model are similar to those of the original k-omega model, but without the undesirable freestream dependency. The predictions of the SST model are also independent of the freestream values and show excellent agreement with experimental data for adverse pressure gradient boundary-layer flows.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-TM-103975 , A-92183 , NAS 1.15:103975
    Format: application/pdf
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  • 7
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    A comparison of turbulence models in computing multi-element airfoil flows (1994)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Four different turbulence models are used to compute the flow over a three-element airfoil configuration. These models are the one-equation Baldwin-Barth model, the one-equation Spalart-Allmaras model, a two-equation k-omega model, and a new one-equation Durbin-Mansour model. The flow is computed using the INS2D two-dimensional incompressible Navier-Stokes solver. An overset Chimera grid approach is utilized. Grid resolution tests are presented, and manual solution-adaptation of the grid was performed. The performance of each of the models is evaluated for test cases involving different angles-of-attack, Reynolds numbers, and flap riggings. The resulting surface pressure coefficients, skin friction, velocity profiles, and lift, drag, and moment coefficients are compared with experimental data. The models produce very similar results in most cases. Excellent agreement between computational and experimental surface pressures was observed, but only moderately good agreement was seen in the velocity profile data. In general, the difference between the predictions of the different models was less than the difference between the computational and experimental data.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 94-0291 , Jan 10, 1994 - Jan 13, 1994; Reno, NV; United States|; 13 p.
    Format: text
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    NASA TECHNICAL REPORTS
  • 8
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    Boundary-layer transition and global skin friction measurement with an oil-fringe imaging technique (1993)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A new oil-fringe imaging fkin friction (FISF) technique to measure skin friction on wind tunnel models is presented. In the method used to demonstrate the technique, lines of oil are applied on surfaces that connect the intended sets of measurement points, and then a wind tunnel is run so that the oil thins and forms interference fringes that are spaced proportional to local skin friction. After a run the fringe spacings are imaged with a CCD-array digital camera and measured on a computer. Skin friction and transition measurements on a two-dimensional wing are presented and compared with computational predictions.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: SAE PAPER 932550 , (ISSN 0148-7191); 15 p.|SAE, Aerotech ''93; Sep 27, 1993 - Sep 30, 1993; Costa Mesa, CA; United States
    Format: text
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  • 9
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    Hypersonic flows as related to the National Aerospace Plane (1995)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The object of Cooperative Agreement NCC2-452 was to identify, develop, and document reliable turbulence models for incorporation into CFD codes, which would then subsequently be incorporated into numerical design procedures for the NASP and any other hypersonic vehicles. In a two-pronged effort, consisting of an experimental and a theoretical approach, several key features of flows over complex vehicles were identified, and test bodies were designed which were composed of simple geometric shapes over which these flow features were measured. The experiments were conducted in the 3.5' Hypersonic Wind Tunnel at NASA Ames Research Center, at nominal Mach numbers from 7 to 8.3 and Re/m from 4.9 x 10(exp 6) to 5.8 x 10(exp 6). Boundary layers approaching the interaction region were 2.5 to 3.7 cm thick. Surface and flow field measurements were conducted, and the initial boundary conditions were experimentally documented.
    Keywords: AERODYNAMICS
    Type: NASA-CR-199365 , NAS 1.26:199365
    Format: application/pdf
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  • 10
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    Zonal Two Equation Kappa-Omega Turbulence Models for Aerodynamic Flows (1993)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Two new versions of the kappa-omega two-equation turbulence model will be presented. The new Baseline (BSL) model is designed to give results similar to those of the original kappa-omega model of Wilcox, but without its strong dependency on arbitrary freestream values. The BSL model is identical to the Wilcox model in the inner 50% of the boundary-layer but changes gradually to the standard kappa-epsilon model (in a kappa- omega formulation) towards the boundary-layer edge. The free shear layers. The second version of the model is called Shear-Stress Transport (SST) model. It is a variation of the BSL model with the additional ability to account for the transport of the principal turbulent shear stress in adverse pressure gradient boundary-layers. The model is based on Bradshaw's assumption that the principal shear-stress is proportional to the turbulent kinetic energy, which is introduced into the definition of the eddy-viscosity. Both models are tested for a large number of different flowfields. The results of the BSL model are similar to those of the original kappa-omega model, but without the undesirable freestream dependency. The predictions of the SST model are also independent of the freestream values but show better agreement with experimental data for adverse pressure gradient boundary-layer flows.
    Keywords: Aerodynamics
    Type: NASA-TM-111629 , NAS 1.15:111629 , AIAA Paper 93-2906 , AIAA Fluid Dynamics Conference; Jul 06, 1993 - Jul 09, 1993; Orlando, FL; United States
    Format: application/pdf
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