Application of Simcenter STAR-CCM+ for analysis of CFD sensitivities in NASA Juncture Flow Simulation

Zastawny, Marian; Lardeau, Sylvain

doi:10.2514/6.2020-2736

Cited by 3 publications

(3 citation statements)

References 27 publications

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“…This finding justifies the design objectives of this study, in order to obtain useful results concerning the junction flow response to the junction region design modifications. This conclusion can be also supported by the current literature that indicates the SST k-ω tendency to over predict corner separations at junction flows, and at the same time that the RSM can dramatically under predict the separation size [28]. The above findings make the authors confident to conclude about the corner separation occurrence, but of course not about its exact size.…”

Section: Governing Equations and Turbulence Modellingsupporting

confidence: 73%

“…Several articles demonstrate the need for non-linear -closure turbulence models [21][22][23][24][25][26][27][28][29] for junction flow investigations, where corner separation is present. For this reason two turbulence models were used in the present work, the SST (Shear Stress Transport) k-ω model [20,[30][31][32][33][34], appropriately modified for the purpose of this work, and the second order Reynolds-Stress Model (RSM) [33][34][35].…”

Section: Governing Equations and Turbulence Modellingmentioning

confidence: 99%

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Mathematical Modelling and Comparative Numerical Simulations of Swing-Fuselage Junction Vortex Structures

S¹,

NC²

2022

J Aerosp Eng Mech

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Turbulence and flow disturbances occurring at the aircraft wing-fuselage junction cause a deterioration of its aerodynamic performance and an increase in the aircraft's drag force. However, the aircraft junction regions are currently designed empirically due to the lack of knowledge of detailed junction flow dynamics, which consequently leads to less efficient flow management and poorer aerodynamic characteristics. The main objective of the present mathematical-modelling study is research on an aerodynamically enhanced design approach, concerning the improvement of the characteristics of the junction flow and its vortices. Numerical simulations are performed under the prism of vortices' structure formation and patterns, particularly of the horseshoe and corner separation vortices, which dominate such flows. More specifically, this research study proposes a new junction flow parameter, which has been employed in combination with the existing ones, in order to result in a more streamlined and efficient junction design, and investigates the junction flow response, when the reference junction design of a wing-fuselage system is modified by the addition of "fillet", "strake" and "blending" geometry types on the wing. Flow simulations are performed in steady-state mode, at transonic flight regime and at 2° angle of attack, using two turbulence models: The Reynolds Averaged Navier-Stokes (RANS) SST k-ω turbulence model, enhanced with rotation/curvature corrections (SST-CC) and with eddy viscosity and turbulence production limiters, and the second-order closure Reynolds Stress model. The geometrical modifications that were implemented proved to be efficient and their application in the design process of modern aircraft foreshadows the possibility of achieving enhancedperformance flights. More specifically, all the three modifications of the reference geometry increased the aircraft's aerodynamic efficiency, by improving the flow pattern around the wing-fuselage regions at the studied flight state. The most promising configuration proved to be the one which combined the "fillet" and "strake" geometries, resulting in the highest aerodynamic efficiency, by greatly weakening the horseshoe vortex and eliminating the corner separation.

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Section: Governing Equations and Turbulence Modellingsupporting

confidence: 73%

Section: Governing Equations and Turbulence Modellingmentioning

confidence: 99%

Mathematical Modelling and Comparative Numerical Simulations of Swing-Fuselage Junction Vortex Structures

S¹,

NC²

2022

J Aerosp Eng Mech

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“…Its excellent performance has been extensively studied in the external flow. [19][20][21][22] However, its application in the internal flow is still relatively small. In this paper, several internal flow cases will be investigated, the latest QCR correction (QCR2020) model is applied to SA and SST turbulence models, and four commonly used validation cases, namely, the square duct, compression corner, S-duct, and isolator, are numerically calculated and compared with their experimental values.…”

Section: Introductionmentioning

confidence: 99%

Validation and analyses of QCR correction turbulence model in sub-/super-sonic inner flows

Wang,

Gu,

Zhang

et al. 2023

Proceedings of the Institution of Mechanical Engineers, Part G:

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The inlet, isolation section, and other internal flow components are important parts of the aircraft propulsion system. Their performances affect the stability of the entire propulsion system. According to those components, complicated shock wave/boundary layer interaction (SBLI), flow separation, and secondary flow phenomena would occur. The commonly used turbulence models, SA and SST, cannot predict the anisotropy of turbulence. This deficiency makes the calculated results differ significantly from the experimental results and cannot accurately predict their aerodynamic performance. This paper validates the feasibility and effectiveness of the turbulence models based on quadratic constitutive relation (QCR) correction applied to the flow of square duct, compression corners, diffusing 3D S-Duct, and axisymmetric cylindrical isolator. This can support future calculations of complex flow fields with flow separation and secondary flow phenomena in the subsonic or supersonic inlet. The results show that the turbulence model with QCR correction is better than the original turbulence model. Among them, the SA-QCR2020 turbulence model is the best, which is able to predict the presence of secondary flows and large boundary layer separated flows well.

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Analysis of a Wildfire and Smoke Propagation Model at Chiak Mountain Using Computational Fluid Dynamics

Kim¹,

Kang²

2022

J. Korean Soc. Hazard Mitig

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This study analyzed the arrival time and diffusion pattern of a wildfire at Chiak Mountain, Wonju, Korea. Simcenter STAR-CCM+, which is a computational fluid dynamics program, was used to analyze flow fields generated by mountain topography and to create a combustion model. The size of the area under study was 16 km², and ignition was conducted at the first campsite. Approximately six million mesh were generated. The temperature and propagation of soot were analyzed for 1 h after the simulation was started. Implicit unsteady analysis was used for time-dependent diffusion, and molecular diffusivity was used for flow field analysis. The results were as follows. 1) The spread of the wildfire was affected by the stack effect derived from the wind direction and mountain topography. 2) Approximately 22 min were required for the wildfire to spread from the campground to a western point 500 m away, and the average temperature was 1,200 ℃ or higher. 3) The spread of the wildfire and soot caused by the difference between the ignition and flash points of the wildfire became faster over time.

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Application of Simcenter STAR-CCM+ for analysis of CFD sensitivities in NASA Juncture Flow Simulation

Cited by 3 publications

References 27 publications

Mathematical Modelling and Comparative Numerical Simulations of Swing-Fuselage Junction Vortex Structures

Mathematical Modelling and Comparative Numerical Simulations of Swing-Fuselage Junction Vortex Structures

Validation and analyses of QCR correction turbulence model in sub-/super-sonic inner flows

Analysis of a Wildfire and Smoke Propagation Model at Chiak Mountain Using Computational Fluid Dynamics

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