Unsteady Flow Simulation of a High-Lift configuration using a Lattice Boltzmann Approach

Fares, Ehab; Noelting, Swen

doi:10.2514/6.2011-869

Cited by 58 publications

(47 citation statements)

References 25 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…The computational method is based on a Lattice Boltzmann Method (LBM) [30][31] . The inherent low numerical dissipation scheme is suitable for aeroacoustics applications.…”

Section: Methodsmentioning

confidence: 99%

Computational and Experimental Study on Noise Generation from Tire-Axle Regions of a Two-Wheel Main Landing Gear

Murayama

Yokokawa

Kato

et al. 2011

17th AIAA/CEAS Aeroacoustics Conference (32nd AIAA Aeroacoustics Conference)

View full text Add to dashboard Cite

The purpose of this paper is computational and experimental investigation of flowfield related to noise generation mechanism from tire-axle regions of a two-wheel main landing gear. Flowfield around tire-axle is complicated with the existence of complicated geometries such as torque link, brake-caliper, and wheel cap. The unsteady flowfields around tire-axle are investigated with change of the torque link setting by unsteady CFD computations on the detail geometry. Three configurations; (1) baseline configuration with backward torque link, (2) configuration without torque link, and (3) configuration with forward torque link are computed. The contributions to the noise level and the directivity of the noise are investigated by the computations and far-field noise measurements. By the computations and wind tunnel tests, the characteristics and physics of the noise from the tire-axle regions of a two-wheel main landing gear are discussed. NomenclatureC P = pressure coefficient FW-H = Ffowcs Williams and Hawkings OASPL = overall sound pressure level R Aircraft = distance to evaluation location of far field noise at aircraft-scale R Model = distance to evaluation location of far field noise at model-scale Re = Reynolds number RTRI = Large-Scale Anechoic Wind Tunnel in Railway Technical Research Institute SPL = sound pressure level T = free-stream temperature U inf = free-stream velocity U Aircraft = aircraft speed U Model = free-stream velocity of wind tunnel test VR = variable resolution

show abstract

“…The computational method is based on a Lattice Boltzmann Method (LBM) [30][31] . The inherent low numerical dissipation scheme is suitable for aeroacoustics applications.…”

Section: Methodsmentioning

confidence: 99%

Computational and Experimental Study on Noise Generation from Tire-Axle Regions of a Two-Wheel Main Landing Gear

Murayama

Yokokawa

Kato

et al. 2011

17th AIAA/CEAS Aeroacoustics Conference (32nd AIAA Aeroacoustics Conference)

View full text Add to dashboard Cite

show abstract

“…The turbulence model uses a swirl correction to locally reduce the influence of the modeled eddy viscosity to allow vortical structures to develop and persist without added artificial damping. [15][16][17] In addition, a wall model relying on algebraic general relations such as the logarithmic law of the wall, and extended to account for pressure gradients effects is used to capture the boundary layer behavior and relax the grid spacing requirement near the solid walls. 18 The turbulence modeling approach together with the inherently unsteady nature of the LBM ensures accurate and efficient simulation of the large structures especially in regions of separated flows and shows conceptual similarities with the recent DDES approach of Spalart.…”

Section: Simulation Methodsmentioning

confidence: 99%

Numerical Simulation of Fluidic Actuators for Flow Control Applications

Vatsa

Köklü

Wygnanski

et al. 2012

6th AIAA Flow Control Conference

View full text Add to dashboard Cite

Active flow control technology is finding increasing use in aerospace applications to control flow separation and improve aerodynamic performance. In this paper we examine the characteristics of a class of fluidic actuators that are being considered for active flow control applications for a variety of practical problems. Based on recent experimental work, such actuators have been found to be more efficient for controlling flow separation in terms of mass flow requirements compared to constant blowing and suction or even synthetic jet actuators. The fluidic actuators produce spanwise oscillating jets, and therefore are also known as sweeping jets. The frequency and spanwise sweeping extent depend on the geometric parameters and mass flow rate entering the actuators through the inlet section. The flow physics associated with these actuators is quite complex and not fully understood at this time. The unsteady flow generated by such actuators is simulated using the lattice Boltzmann based solver PowerFLOW R . Computed mean and standard deviation of velocity profiles generated by a family of fluidic actuators in quiescent air are compared with experimental data. Simulated results replicate the experimentally observed trends with parametric variation of geometry and inflow conditions. Nomenclature

show abstract

“…Transition tended to reduce trailing edge flap separation and significantly improve pitching moment predictions. Subsequently, the papers of Steed, 6 Fares and Nolting, 11 and Eliasson et al 9,17 explored the important effects of including transition in the CFD simulations. Steed used the 4-equation γ-Re θ SST transition/turbulence model of Langtry and Menter.…”

Section: Introductionmentioning

confidence: 99%

“…[5][6][7][8][9][10][11][12][13][14][15][16][17][18] Most of these studies involved a few wellknown "standard" turbulence models such as Spalart-Allmaras (SA) 19 and Menter's shear-stress transport (SST) 20 applied in fully turbulent mode. At the workshop, SA (fully turbulent) was heavily favored because it tended to yield closer agreement to experiment for the Trapezoidal Wing.…”

Section: Introductionmentioning

confidence: 99%

NASA Trapezoidal Wing Computations Including Transition and Advanced Turbulence Modeling

Rumsey

Lee-Rausch

2015

Journal of Aircraft

View full text Add to dashboard Cite

Flow about the NASA Trapezoidal Wing is computed with several turbulence models by using grids from the first High Lift Prediction Workshop in an effort to advance understanding of computational fluid dynamics modeling for this type of flowfield. Transition is accounted for in many of the computations. In particular, a recently-developed 4-equation transition model is utilized and works well overall. Accounting for transition tends to increase lift and decrease moment, which improves the agreement with experiment. Upper surface flap separation is reduced, and agreement with experimental surface pressures and velocity profiles is improved. The predicted shape of wakes from upstream elements is strongly influenced by grid resolution in regions above the main and flap elements. Turbulence model enhancements to account for rotation and curvature have the general effect of increasing lift and improving the resolution of the wing tip vortex as it convects downstream. However, none of the models improve the prediction of surface pressures near the wing tip, where more grid resolution is needed.

show abstract

Unsteady Flow Simulation of a High-Lift configuration using a Lattice Boltzmann Approach

Cited by 58 publications

References 25 publications

Computational and Experimental Study on Noise Generation from Tire-Axle Regions of a Two-Wheel Main Landing Gear

Computational and Experimental Study on Noise Generation from Tire-Axle Regions of a Two-Wheel Main Landing Gear

Numerical Simulation of Fluidic Actuators for Flow Control Applications

NASA Trapezoidal Wing Computations Including Transition and Advanced Turbulence Modeling

Contact Info

Product

Resources

About