Validation of a Lattice-Boltzmann Approach for Transonic and Supersonic Flow Simulations

Fares, Ehab; Wessels, Michael; Zhang, Raoyang; Sun, Chi; Gopalaswamy, N.; Roberts, Peter; Hoch, Jamie; Chen, Hufong

doi:10.2514/6.2014-0952

Cited by 39 publications

(17 citation statements)

References 35 publications

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“…12 For the simulations presented in this work, a newly developed transonic beta version of the LBM method was employed, similar to what was described by Fares et al. 5 For a more complete coverage of the scientific basics of the new transonic LBM scheme the reader is referred to [13][14][15].…”

Section: Methodsmentioning

confidence: 99%

“…While some effort were made to extend the range of Mach numbers for LBM, no such tool was available for industrially relevant cases. Only recently, a first validation of an extended LBM scheme in the PowerFLOW code was published by Fares et al 5 that opened up the range of flow velocities from purely subsonic up to supersonic Mach numbers. As a further step in the validation process, a similar method is now applied to and validated on a transonic aircraft configuration.…”

Section: Introductionmentioning

confidence: 99%

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Validation of a Transonic Lattice-Boltzmann Method on the NASA Common Research Model

König¹,

Fares²

2016

54th AIAA Aerospace Sciences Meeting

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A novel transonic Lattice-Boltzmann Method is validated against the NASA Common Research Model. This model offers the most comprehensive experimental data base available but also suffers from a number of issues that make a comparison to CFD difficult. In order to achieve a rigorous validation of the new code, the major effects present in the wind tunnel experiments are included in the modeling. This work describes Lattice-Boltzmann simulations of the Common Research Model with updated wing twist distributions and including the wind tunnel support system. Preliminary results for both the baseline geometry and the updated model are presented and show a promising correlation to the experiments.

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Section: Methodsmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Validation of a Transonic Lattice-Boltzmann Method on the NASA Common Research Model

König¹,

Fares²

2016

54th AIAA Aerospace Sciences Meeting

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“…32, 33 and 40 is used. All of the results presented here were obtained using the fully compressible version of the PowerFLOW R code, [41][42][43] which can be run in low speed, high subsonic or transonic mode. No-actuation, and lower pressure ratio cases are run using the high subsonic mode of the PowerFLOW R code.…”

Section: Simulation Methodsmentioning

confidence: 99%

Numerical Simulation of a Simplified High-Lift CRM Configuration Embedded with Fluidic Actuators

Vatsa

Duda²,

Lin

et al. 2018

2018 Applied Aerodynamics Conference

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Numerical simulations have been performed for a simplified high-lift configuration that is representative of a modern transport airplane. This configuration includes a leading-edge slat, fuselage, wing, nacelle-pylon and a simple hinged flap. The suction surface of the flap is embedded with multiple rows of fluidic actuators to reduce the extent of reversed flow regions and improve the aerodynamic performance of the configuration with flap in a deployed state. In the current paper, a Lattice Boltzmann Method based high-fidelity computational fluid dynamics (CFD) code, known as PowerFLOW R is used to simulate the entire flow field associated with this configuration, including the flow inside the actuators. A fully compressible version of the PowerFLOW R code that has been validated for high speed flows is used for the present simulations to accurately represent the transonic flow regimes that are encountered in the flow field generated by the actuators operating at higher mass flow (momentum) rates required to mitigate reverse flow regions on the suction surfaces of the main wing and the flap. The numerical solutions predict the expected trends in aerodynamic forces as the actuation levels are increased. More efficient active flow control (AFC) systems and actuator arrangement for lift augmentation are emerging based on the parametric studies conducted here prior to wind tunnel tests. These numerical solutions will be compared with experimental data, once such data becomes available.

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“…Recent extensions of the scheme recover a fully unsteady compressible form of the Navier-Stokes equations. [37][38][39] Applications of this new version at transonic conditions were presented in recent papers by Koeing and Fares 40 for the NASA CRM, and by Duda et al 41 for a sweeping jet (fluidic) actuator operating at choked conditions. The newer version of the PowerFLOW R code, which incorporates the modified LBM scheme suitable for simulating flows containing transonic flow regimes, has two options for higher-speed flows: the high-subsonic option for 0.5 < Mach < 0.9, and a transonic option for 0.9 < Mach < 2.0.…”

Section: Simulation Methodologymentioning

confidence: 99%

Noise Simulations of the High-Lift Common Research Model

Lockard

Choudhari

Vatsa

et al. 2017

23rd AIAA/CEAS Aeroacoustics Conference

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The PowerFLOW R code has been used to perform numerical simulations of the high-lift version of the Common Research Model (HL-CRM) that will be used for experimental testing of airframe noise. Time-averaged surface pressure results from PowerFLOW R are found to be in reasonable agreement with those from steady-state computations using FUN3D. Surface pressure fluctuations are highest around the slat break and nacelle/pylon region, and synthetic array beamforming results also indicate that this region is the dominant noise source on the model. The gap between the slat and pylon on the HL-CRM is not realistic for modern aircraft, and most nacelles include a chine that is absent in the baseline model. To account for those effects, additional simulations were completed with a chine and with the slat extended into the pylon. The case with the chine was nearly identical to the baseline, and the slat extension resulted in higher surface pressure fluctuations but slightly reduced radiated noise. The full-span slat geometry without the nacelle/pylon was also simulated and found to be around 10 dB quieter than the baseline over almost the entire frequency range. The current simulations are still considered preliminary as changes in the radiated acoustics are still being observed with grid refinement, and additional simulations with finer grids are planned. Nomenclature C p coefficient of pressure c local deployed chord p pressure rms root mean square VR variable resolution x, y, z Cartesian coordinates Superscript: ′ perturbation quantity (e.g., p ′ = p − p o) Subscript: o dimensional reference quantity

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Validation of a Lattice-Boltzmann Approach for Transonic and Supersonic Flow Simulations

Cited by 39 publications

References 35 publications

Validation of a Transonic Lattice-Boltzmann Method on the NASA Common Research Model

Validation of a Transonic Lattice-Boltzmann Method on the NASA Common Research Model

Numerical Simulation of a Simplified High-Lift CRM Configuration Embedded with Fluidic Actuators

Noise Simulations of the High-Lift Common Research Model

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