Development and application of Spalart–Allmaras one equation turbulence model to three-dimensional supersonic complex configurations

Deck, Sébastien; Duveau, Philippe; d'Espiney, Paulo; Guillen, Philippe

doi:10.1016/s1270-9638(02)01148-3

Cited by 127 publications

(64 citation statements)

References 13 publications

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“…[19]. In model assumption, the eddy viscosity is considered as the capability of turbulent flow to transport momentum.…”

Section: Flight Physics -Models Techniques and Technologiesmentioning

confidence: 99%

Airfoil Boundary Layer Optimization Toward Aerodynamic Efficiency of Wind Turbines

Kim¹,

Al-Abadi²,

Delgado³

2018

Flight Physics - Models, Techniques and Technologies

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This chapter describes the method of airfoil optimization considering boundary layer for aerodynamic efficiency increment. The advantages of laminar boundary layer expansion in airfoil of horizontal axis wind turbine (HAWT) blades are presented as well. The genetic algorithm (GA) optimization interfaced with the flow solver XFOIL was used with multiobjective function. The power performance of turbine with optimized airfoil was calculated by using blade element method (BEM) in software QBlade. The CFD simulation from OpenFOAM ® with Spalart-Allmaras turbulence model showed the visualized airflow. The optimized airfoil shows enlarged laminar boundary layer region in all flow regime with a higher aerodynamic efficiency and the increased gliding ratio (GR). The power velocity and annual energy production (AEP) curves show the performance improvement of wind turbine with the optimized airfoil. The boundary layer thickness and skin-friction coefficient values support the decreased drag of the optimized airfoil. The smaller laminar separation bubbles and reduced stall regime of CFD simulations illustrate the desirable aerodynamics of the resulted airfoil.

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“…[19]. In model assumption, the eddy viscosity is considered as the capability of turbulent flow to transport momentum.…”

Section: Flight Physics -Models Techniques and Technologiesmentioning

confidence: 99%

Airfoil Boundary Layer Optimization Toward Aerodynamic Efficiency of Wind Turbines

Kim¹,

Al-Abadi²,

Delgado³

2018

Flight Physics - Models, Techniques and Technologies

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“…The DES investigation of turbulence at a circular pier with scour hole has been carried out (Kirkil, Constantinescu, & Ettema, 2009). Spalart-Allmaras One-Equation Turbulence (Deck, S. Duveau, P., d'Espiney & Guillen, 2002). A DES for turbulent flows in a pipe with a snowflake fractal orifice has been learned (Nicolleau et al, 2012).…”

Section: Turbulence Q-criterion Algorithm and Fuselage Effect Theorymentioning

confidence: 99%

The Flow Visualization CFD Studies of the Fuselage and Rolled-up Vortex Effects of the Chengdu J-10-like Fighter Canard

Sutrisno¹,

Rochmat²,

Wibowo³

et al. 2018

MAS

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Fighter aircrafts with high maneuverability and swiftness are due to fuselage effects, caused by canard-fuselage-main wing configuration. Even though the flows around fighters are highly complex, mostly they create rolled-up vortices capable to delay stalls and increase maximum lifts (Calderon, Wang & Gursul, 2012;Mitchell & Delery, 2001;Boelens, 2012;Chen, Liu, Guo & Qu, 2015). The vortex dynamics analysis method employment is introduced, in this case we focus only on the fighter canard. It characterizes the vortex core, develops the pitching moment & main wing total lift, and exploits the vortex centre visualization, the strength, negative surface pressure and its trajectory. This paper explains the influence of the fighter fuselage, it generates rolled-up vortex effects, causes the flow deflected by the fighter fuselage head, strengthen the vortex centre to become vortex core. Above the aircraft head, due to the curved contour head effect, the second vortex centers are developed makes the vortex center above the head more dynamic.Comparing with fighter without fuselage, the flow property changes, for Chengdu J-10-like model with fuselage, are concentrated at the canard leading edge, where the negative pressures are stronger, since the maximum axial velocities of the vortex centre are higher, and give more distinctive vortex breakdown locations.

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“…The inlet does not provide any incoming droplets and the details of the used boundary conditions are given in Table 1. A one-equation Spalart-Allmaras turbulence (Deck, Duveau, d'Espiney, & Guillen, 2002) was used to simulate turbulence flow, and the result of the single-phase flow was used as the initial value of the multi-phase calculation for numerical stability.…”

Section: Moore Nozzle B (Moore Et Al 1973)mentioning

confidence: 99%

“…The maximum y+ values with the grid are 0.18 and 0.20 for case 252 and case 257, respectively. Similar settings to those used for the Moore nozzle were used for the boundary conditions (Table 2) and a Spalart-Allmaras turbulence model for compressible flows was adopted (Deck et al, 2002). Single-phase calculations were performed before the wet-steam calculation for initialization.…”

Section: Moses and Stein Nozzle (Cases 252 And 257; Moses And Stein 1978)mentioning

confidence: 99%

“…Singlephase calculations were used as the initial values of the multi-phase calculations. Again, a Spalart-Allmaras turbulence model for compressible flows was adopted (Deck et al, 2002). In White (1992), the pressure on the blade surface and the wetness at the traverse plane were measured, but only the surface pressure was used in the comparison due to the unspecified traverse plane location.…”

Section: White Cascade (White 1992)mentioning

confidence: 99%

See 1 more Smart Citation

Numerical analysis of non-equilibrium steam condensing flows in various Laval nozzles and cascades

Kim

Park

Kim

et al. 2017

Engineering Applications of Computational Fluid Mechanics

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When steam is used in fluid machinery, phase transition can occur that affects not only the flow fields but also machine performance. Therefore, to achieve an accurate prediction of steam condensing flow using computational fluid dynamics (CFD), phase-transition phenomena should be considered and a non-equilibrium wet-steam model is required. Such a model is implemented in this study using the in-house code T-Flow, and the flow fields -including phase-transition phenomena -in various Laval nozzles are examined. The results for multi-phase flows can be obtained in relatively short time by using mixture assumption and an inner-iteration method. The calculated results reflect the characteristics of the condensing flows well and are comparable with those obtained experimentally. Also, it was found that the superheating level of incoming steam can explain the tendency of condensation in the nozzles considered in a simple way. In addition, steam condensing flows in the blade cascades were simulated. As a result, the predicted blade loading agreed well with the experimental data and the superheating level at inlet was responsible for the condensation trend not only in the nozzles but also in the cascades. In future work, the characteristics of steam condensing flow in a steam turbine where complex flows and phase transition occur can be investigated using the presented model. ARTICLE HISTORY

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Development and application of Spalart–Allmaras one equation turbulence model to three-dimensional supersonic complex configurations

Cited by 127 publications

References 13 publications

Airfoil Boundary Layer Optimization Toward Aerodynamic Efficiency of Wind Turbines

Airfoil Boundary Layer Optimization Toward Aerodynamic Efficiency of Wind Turbines

The Flow Visualization CFD Studies of the Fuselage and Rolled-up Vortex Effects of the Chengdu J-10-like Fighter Canard

Numerical analysis of non-equilibrium steam condensing flows in various Laval nozzles and cascades

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