Experimental Study of Slat Noise from 30P30N Three-Element High-Lift Airfoil in JAXA Kevlar-Wall Low-Speed Wind Tunnel

Murayama, Mitsuhiro; Yokokawa, Yuzuru; Ura, Hiroki; Nakakita, Kazuyuki; Yamamoto, Kazuomi; Ito, Yasushi; Takaishi, Takehisa; Sakai, Ryotaro; Shimoda, Kei; Kitasaka, Takayuki; Homma, Tomoyuki

doi:10.2514/6.2018-3460

Cited by 36 publications

(29 citation statements)

References 7 publications

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“…However, over the course of the past 20 years, several universities have been commissioning aeroacoustic wind tunnels of varying sizes and capabilities [19][20][21][22][23][24][25][26][27][28]. More recently, Kevlar-walled anechoic wind tunnel test sections have been designed and implemented [8,28,29], which improves the aerodynamic performance of the wind tunnel, while keeping the flow acous-2 tically accessible.…”

Section: Introductionmentioning

confidence: 99%

Design and performance of an aeroacoustic wind tunnel facility at the University of Bristol

Mayer¹,

Jawahar²,

Szoke

et al. 2019

Applied Acoustics

107

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This paper provides an overview of the design and performance of the new aeroacoustic wind tunnel facility at the University of Bristol. The purpose of the facility is to enable near-and far-field acoustic and aerodynamic studies on a variety of different aerodynamic components and to examine diverse noise control techniques. The facility comprises a large acoustic chamber, anechoic down to 160 Hz, and a temperature controlled closed-circuit wind tunnel with an open test section. The wind tunnel features two interchangeable rectangular nozzles with a partially shared contraction. Both nozzles are shown to possess a high flow quality with high flow uniformity and low turbulence intensity of 0.09% and 0.12% for the smaller and larger nozzle, respectively. The maximum attainable flow speeds are 40 m/s for the larger nozzle and 120 m/s for the smaller nozzle corresponding to Reynolds numbers of 2.7 million and 8.1 million per meter, respectively. In this paper, we will present various aerodynamic and acoustic results to characterize the performance of the facility. The background noise levels are found to be sufficiently low and the far-field noise measurements from a flat plate, a round cylinder and a NACA 0012 airfoil compare favorably to existing experimental observations.

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Section: Introductionmentioning

confidence: 99%

Design and performance of an aeroacoustic wind tunnel facility at the University of Bristol

Mayer¹,

Jawahar²,

Szoke

et al. 2019

Applied Acoustics

107

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“…The lift coefficients in this study and the θ-sweep of that in the experiment in Reference [23] are shown in Figure 10. The Cartesian cut-cell simulation with the wall-stress model accurately predicts the lift coefficient.…”

Section: Simulation Results By Wall-modelled Navier-stokes Simulationmentioning

confidence: 83%

“…The flow conditions are provided in Table 3. The chord length c of the 30P30N high-lift airfoil configuration is 0.457 m following the experiment by Murayama et al [23]. The grid system consists of a uniform grid domain and a non-uniform grid domain in the xy direction.…”

Section: Simulation Conditionsmentioning

confidence: 99%

Prediction Capability of Cartesian Cut-Cell Method with a Wall-Stress Model Applied to High Reynolds Number Flows

et al. 2020

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The Cartesian cut-cell method is one of the most promising methods for computational fluid dynamics due to its sharp interface treatment. However, the Cartesian cut-cell method and other Cartesian mesh solvers have difficulty with concentrating grid to boundary layers. The wall-modelling of shear stress is one of the most effective methods to reduce computational grids in boundary layers. This study investigated the applicability of a wall-stress model to the Cartesian cut-cell method. In the numerical simulations of the flow around a triangular column, Cartesian cut-cell simulation with the wall-stress model adequately predicted the drag coefficient. In the numerical simulations of the flow around a 30P30N high-lift airfoil configuration, the Cartesian cut-cell simulation with the wall-stress model adequately predicts the lift coefficient. The intermittent vortex structure of the outer layer of the turbulent boundary layer was observed on the suction side of the main element and the flap. The Cartesian cut-cell method with a wall-stress model is useful for predicting high Reynolds number flows at R e ∼ 10 6 .

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“…Good agreement in the near-field PSD predictions at ↵ = 5.5 degrees with BANC-III workshop results also carries over at the larger angles of attack when comparing to the more recent 2m ⇥ 2m Kevlar-wall JAXA wind tunnel results. 1 Figures 13, 14, 15, and 16 plot the near-field PSD spectrum from the current simulations along with JAXA wind tunnel results at four distinct sensor locations and all three-angles of attack. Note comparisons with wind tunnel data include two bounding angles of attack to account for the expected shift in lift coe cient with angle of attack caused by severe blockage e↵ects in the wind-tunnel.…”

Section: Vb Near-field Power Spectral Densitymentioning

confidence: 99%

“…In BANC-V, two additional angles of attack, ↵ = 9.5 and 14.0 degrees were added to the problem description, in part due to the high quality acoustic data recently obtained in the 2m ⇥ 2m Kevlar-wall wind tunnel at the Japan Aerospace Exploration Agency (JAXA). 1 The authors have been consistent contributors to the workshop since BANC-III, and the Category 7 Slat Noise case has been a driving stimulus to several modeling and simulation enhancements within the Launch Ascent and Vehicle Aerodynamics (LAVA) solver framework. 14 In addition to the BANC workshop contributions on slat noise, an installed version of the 30P30N with a retracted flap which was studied experimentally in the open-jet Quiet Flow Facility (QFF) at NASA Langley Research Center, 15 was also analyzed computationally using the LAVA solver.…”

Section: Introductionmentioning

confidence: 99%

Predictions of Slat Noise from the 30P30N at High Angles of Attack using Zonal Hybrid RANS-LES

Housman

Stich

Kiris

2019

25th AIAA/CEAS Aeroacoustics Conference

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Aeroacoustic predictions of slat noise from the 30P30N three-element high-lift system at high angles of attack are presented using a zonal hybrid RANS-LES method. The simulations are part of the 5 th AIAA Benchmark problems for Airframe Noise Computations (BANC-V) Workshop. An economical approach utilizing structured overset grids with spatially varying span-wise grid resolution and a high-order accurate finite di↵erence method is described. The method is utilized for near-field predictions at three angles of attack: ↵ = 5.5, 9.5, and 14.0 degrees. Far-field noise is obtained by propagating the nearfield solution using a permeable surface Ffowcs Williams-Hawkings (FWH) method. Good agreement is obtained with both near-field and far-field Power Spectral Density (PSD) data from an experimental study of the 30P30N in the 2m⇥2m Kevlar-wall wind tunnel at the Japan Aerospace Exploration Agency (JAXA). 1 Specifically, the reduction in narrow band peaks and overall broadband noise levels with increasing angle of attack is captured well using the zonal hybrid RANS-LES method.

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Experimental Study of Slat Noise from 30P30N Three-Element High-Lift Airfoil in JAXA Kevlar-Wall Low-Speed Wind Tunnel

Cited by 36 publications

References 7 publications

Design and performance of an aeroacoustic wind tunnel facility at the University of Bristol

Design and performance of an aeroacoustic wind tunnel facility at the University of Bristol

Prediction Capability of Cartesian Cut-Cell Method with a Wall-Stress Model Applied to High Reynolds Number Flows

Predictions of Slat Noise from the 30P30N at High Angles of Attack using Zonal Hybrid RANS-LES

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