An Application of Local Correlation-Based Transition Model to JAXA High-Lift Configuration Model

Abstract In this paper, we present a new local-correlation based zero-equation transition model. The new model, which is derived from the local-correlation based one-equation gamma transition model (Menter, F. R., Smirnov, P. E., Liu, T., and Avancha, R., A One-Equation Local Correlation-Based Transition Model, Flow, Turbulence and Combustion, vol. 95, 2015, pp. 583619.), does not require any additional equation to be solved, by defining a new variable, which captures the turbulent kinetic energy and intermittency collectively. The new model only adds three more source terms to the existing transport equation of turbulent kinetic energy. Hence the new model is straightforward to implement in already existing RANS solvers and reduces the computational memory requirement as compared to the other transition models. The transition prediction capability of the new model is tested and compared against the one-equation gamma transition model, especially for turbomachinery applications, where bypass transition is the primary transition mechanism, using a standard flat plate test case, and S809 airfoil. Preliminary results show that the new zero-equation transition model produces satisfactory results in terms of transition-location prediction.

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RANS Simulation Over JAXA High-Lift Configuration Model Using Spectral Volume Method

38th Fluid Dynamics Conference and Exhibit ◽

10.2514/6.2008-4308 ◽

2008 ◽

Author(s):

Takanori Haga ◽

Michiko Furudate ◽

Keisuke Sawada ◽

Akihisa Masunaga

Keyword(s):

Configuration Model ◽

High Lift ◽

Rans Simulation ◽

Spectral Volume ◽

Volume Method

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Hybrid-Grid Simulation of Unsteady Wake-Boundary Layer Interaction on a High Lift Low Pressure Turbine Airfoil

Volume 6: Turbo Expo 2007, Parts A and B ◽

10.1115/gt2007-28111 ◽

2007 ◽

Cited By ~ 3

Author(s):

Hong Yang ◽

Thomas Roeber ◽

Dragan Kozulovic

Keyword(s):

Boundary Layer ◽

Vortex Street ◽

Transition Model ◽

Mode Transition ◽

Suction Surface ◽

High Lift ◽

Unsteady Wake ◽

Boundary Layer Interaction ◽

Hybrid Grid ◽

Multi Mode

The unsteady wake-boundary layer interaction on a high lift low pressure (LP) turbine airfoil T106C was investigated by applying the hybrid structured-unstructured RANS solver developed at the DLR. The simulation domain was split into two parts: a translational one with moving bars and a stationary one with turbine airfoils, and in between was a sliding mesh interface. An unstructured grid was generated around the moving bars with particular clustering along the wake path to have a sharp resolution of the shedding vortex street, whereas the stationary blade airfoil subject to the incoming wakes was meshed with a block-structured grid to ease the implementation of the laminar-turbulent transition model around the airfoil. The Wilcox two-equation k-ω turbulence model was applied in conjunction with a multi-mode transition model developed by the authors taking into account several modes of transition, namely natural/bypass, separated-flow and wake-induced transition modes. In this paper, the hybrid-grid modeling is first validated against measurements from the VKI, and then the unsteady flow mechanisms associated with the shedding vortices and the multi-mode transition on the blade airfoil are analyzed. Furthermore, the quasi-steady mixing-plane model on the hybrid grids is also assessed by a comparison with the time-mean of the unsteady state solutions. In particular, different chopping to the incoming vortex street at the blade leading edge is found to have different effects on the separation and transition over the blade suction surface. At the end a composite picture of the boundary-layer development over the suction surface is summarized.

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