Turbulence Modelling Effects on Tandem Cylinder Interaction Flow and Analysis of Installation Effects on Broadband Noise Using Chimera Technique

Greschner, Björn; Eschricht, Dandy; Mockett, Charles; Thiele, Frank

doi:10.2514/6.2012-3033

Cited by 7 publications

(7 citation statements)

References 14 publications

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“…It can be seen from Figure 8 that the surface pressure coefficient of the upstream cylinder is in good agreement with the QFF and BART test results, and the downstream cylinder surface pressure coefficient is closer to the QFF experimental results. This is consistent with the results of literature [18,19]. The main reason for the error at position 80 • and 280 • of the downstream cylinder is that the downstream cylinder is affected by the upstream cylinder, so the flow is more complex, and the spanwise length in the simulation is inconsistent with the experiment.…”

Section: Verification Of Calculation Methodssupporting

confidence: 91%

“…As a fundamental scenario aeroacoustics simulation, tandem cylinders have been studied by many researchers. For instance, different turbulence models were utilized to conduct to numerical simulate [18,19], and the results were compared with the experimental data of NASA achieved from Basic Aerodynamic Research Tunnel (BART) and Quiet Flow Facility (QFF) [20][21][22]. In addition, Dawi [23] used numerical approach to study the acoustic performance of two square cylinders.…”

Section: Introductionmentioning

confidence: 99%

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A Numerical Study of the Wind Speed Effect on the Flow and Acoustic Characteristics of the Minor Cavity Structures in a Two-Wheel Landing Gear

et al. 2021

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The landing gear is widely concerned as the main noise source of airframe noise. The flow characteristics and aerodynamic noise characteristics of the landing gear were numerically simulated based on Large Eddy Simulation and Linearized Euler Equation, and the feasibility of the simulation model was verified by experiments. Then the wind speed effect on the flow and acoustic characteristics of the minor cavity structures in a two-wheel landing gear were analyzed. The results show that the interaction of vortices increases with the increase of velocity at the brake disc, resulting in a slight increase in the amplitude of pressure fluctuation at 55 m·s−1~75 m·s−1. With the increase of speed, the obstruction at the lower hole of torque link decreases, and many vortical structures flow out of the lower hole and are dissipated, so that the pressure fluctuation amplitude of 75 m·s−1 almost does not increase relative to 55 m·s−1. The contribution of each part in the landing gear to the overall noise is as follows: shock strut > tire > torque link > brake disc. At the speed of 34 m·s−1~55 m·s−1, the contribution of each component to the total noise increases with the increase of speed, and the small components such as torque link and brake disc contribute more to the total noise. At the speed of 55 m·s−1~75 m·s−1, the increase of overall noise mainly comes from the main components such as shock strut and tire, and the brake disc and torque link contribute very little to the overall noise. It provides a reference for the further noise reduction optimization design of the landing gear.

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Section: Verification Of Calculation Methodssupporting

confidence: 91%

Section: Introductionmentioning

confidence: 99%

A Numerical Study of the Wind Speed Effect on the Flow and Acoustic Characteristics of the Minor Cavity Structures in a Two-Wheel Landing Gear

et al. 2021

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“…Similar studies have been performed for a tandem cylinder installed in the same facility with similar findings. 40,41 The reference conditions used for the analysis are Mach 0.17 based on the centerline exit velocity of the open-jet and a Reynolds number of 1.7 million based on the stowed chord of 16.73 inches. Standard sea level atmospheric conditions were used for the reference pressure and temperature.…”

Section: Computational Aeroacoustic Analysismentioning

confidence: 99%

Slat Noise Predictions using Higher-Order Finite-Difference Methods on Overset Grids

Housman

Kiris

2016

22nd AIAA/CEAS Aeroacoustics Conference

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Computational aeroacoustic simulations using the structured overset grid approach and higher-order finite di↵erence methods within the Launch Ascent and Vehicle Aerodynamics (LAVA) solver framework are presented for slat noise predictions. The simulations are part of a collaborative study comparing noise generation mechanisms between a conventional slat and a Krueger leading edge flap. Simulation results are compared with experimental data acquired during an aeroacoustic test in the NASA Langley Quiet Flow Facility. Details of the structured overset grid, numerical discretization, and turbulence model are provided.

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“…For the sake of simplicity, we assume that ∂Ω A = Γ N , and hence Γ Z = ∅. The semi-discrete spectral element formulation of problem (5) with numerical integration (SEM-NI) reads: for any time t ∈ (0; T ] find ρ h ∈ V A such that:…”

Section: Discretization Of the Acoustic Problemmentioning

confidence: 99%

“…Following [5], we employ a DDES k − ωSST model to simulate the turbulent flow, see for instance [6] for more details. Acoustic Setup.…”

Section: Turbulent Flow Around a Tandem Cylindermentioning

confidence: 99%

AeroSPEED: a high order acoustic solver for aeroacoustic applications

Artoni¹,

Antonietti²,

Corradi³

et al. 2023

Preprint

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We propose AeroSPEED, a solver based on the Spectral Element Method (SEM) that solves the aeroacoustic Lighthill's wave equation. First, the fluid solution is computed employing a cell centered Finite Volume method. Then, AeroSPEED maps the sound source coming from the flow solution onto the acoustic grid, where finally the Lighthill's wave equation is solved. An ad-hoc projection strategy is adopted to apply the flow source term in the acoustic solver. A model problem with a manufactured solution and the Noise Box test case are used as benchmark for the acoustic problem. We studied the noise generated by the complex flow field around tandem cylinders as a relevant aeroacoustic application. AeroSPEED is an effective and accurate solver for both acoustics and aeroacoustic problems.

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Turbulence Modelling Effects on Tandem Cylinder Interaction Flow and Analysis of Installation Effects on Broadband Noise Using Chimera Technique

Cited by 7 publications

References 14 publications

A Numerical Study of the Wind Speed Effect on the Flow and Acoustic Characteristics of the Minor Cavity Structures in a Two-Wheel Landing Gear

A Numerical Study of the Wind Speed Effect on the Flow and Acoustic Characteristics of the Minor Cavity Structures in a Two-Wheel Landing Gear

Slat Noise Predictions using Higher-Order Finite-Difference Methods on Overset Grids

AeroSPEED: a high order acoustic solver for aeroacoustic applications

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