Towards Accurate Vortex Separation Simulations with RANS Using Improved k-kL Turbulence Model

Date

2023-04-01

Author

Dikbaş, Erdem
Baran, Özgür Uğraş

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This work is licensed under a Creative Commons Attribution-NonCommercial-NoDerivatives 4.0 International License.

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In this study, we present our improved RANS results of the missile aerodynamic flow computation involving leading edge vortex separation. We have used our in-house tailored version of the open source finite volume solver FlowPsi. An ongoing study in the NATO STO Applied Vehicle Technologies Panel (AVT-316) has revealed that a highly maneuverable missile configuration (LK6E2) shows unusual rolling moment characteristics due to the vortex–surface interactions occurring during wing leading edge separation of vortices. We show the performance of the recently developed k- (Formula presented.) turbulence model for this test problem. This turbulence model is shown to have superior capabilities compared to other widely used turbulence models, such as Spalart–Allmaras and shear stress transport. With the k- (Formula presented.) turbulence model, it is possible to achieve more realistic computational results that agree better with the physical data. In addition, we propose improvements to this turbulence model to achieve even better predictions of rolling moment behavior. Modifications based on turbulence production terms in the k- (Formula presented.) turbulence model significantly improved the predicted rolling moment coefficient, in terms of accuracy and uncertainty.

Subject Keywords

k-kL turbulence model, leading-edge flow separation, missile aerodynamics, transonic flow, turbulence modeling, vortex interactions

URI

https://hdl.handle.net/11511/104004

Collections

Department of Mechanical Engineering, Article