INVESTIGATIONS ON SLAT NOISE REDUCTION TECH- NOLOGIES BASED ON PIEZOELECTRIC MATERIAL, PART II: CONTROL SYSTEM DESIGN AND WIND TUNNEL TEST
|
|
- Rolf Turner
- 6 years ago
- Views:
Transcription
1 INVESTIGATIONS ON SLAT NOISE REDUCTION TECH- NOLOGIES BASED ON PIEZOELECTRIC MATERIAL, PART II: CONTROL SYSTEM DESIGN AND WIND TUNNEL TEST Song Xiao, Yu Jinhai, Breard Cyrille and Sun Yifeng Shanghai Aircraft Design and Research Institute (SADRI), COMAC, Shanghai, China Qiu Jinhao and Ji Hongli College of Aerospace Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing, China Aeroacoustic noise from the civil aircraft is not only related to its airworthiness, but also related to the demand of comfort. The noise from slat is the major contribution to the overall airframe noise. Analysis and control of slat noise is of great importance for improving noise environment. A thorough understanding of the flow physics and underlying noise mechanisms is indispensable for prediction, control, and mitigation of slat noise. Two main activities were investigated. Firstly, experiments were performed to investigate the flow field and noise characteristics of a two-element airfoil system. Visualization tests with oil flow, pressure and velocity measurements were carried out in order to investigate the flow characteristic of slat cove. The broadband component and multiple tonal peaks of slat noise were identified by sound intensity technology. Secondly, based on the understanding of the unsteady physics mechanism of the flow in slat cove, a method using active vibration excitation for slat noise control was proposed and validated. The control system was installed at the cusp of slat using piezoelectric (PZT) material in order to disturb the vortex shedding. This paper identifies the slat noise by experiment and reveals active vibration excitation on slat noise reduction. The experimental results show the multiple tonal peaks of slat noise are induced by the feedback mechanism of cavity, and application of the vibration excitation can break the feedback mechanism of slat cove. The proposed control method has an impact on multiple tonal peaks of slat noise and a 4dB reduction in the fourthorder tonal peak was achieved. 1. Introduction With the development of the high-bypass ratio engines in the last decades, aircraft engine noise has come down to a level comparable to airframe noise [1]. Both wind tunnel tests [2][3] and flyover measurements [4][5] have shown that leading-edge slat represents a major source of airframe noise during approach and landing. In recent years, more and more scholars have devoted their efforts to the research of slat noise reduction. Several active and passive control methods have been made on the attenuation of slat noise, but there is an ongoing debate on the application of these technologies. In this paper, the flow physics and underlying noise mechanisms of a three-element airfoil system are summarized in detail. Based on this, a method of active vibration control with piezoelectric fans is introduced and its effectiveness is verified by simulative results both in aspects of aerodynamics and aeroacoustics. 1
2 2. Noise mechanics Slat noise mainly consists of low-frequency broadband noise and high-frequency tonal noise. Major slat noise sources are depicted in figure 1. The high-frequency component is related to the vortex shedding from the finite thickness edge, making contribution to the high-frequency waves. It should be noted that this phenomena is not likely observed at a real full scale model due to the smaller relative edge thickness comparative to a two-dimensional scale model experiments. The low-frequency component is the most prominent component in slat noise spectra in a real aircraft. Although its mechanisms haven t been well understood, a more acceptable view [6] is as follows. The free shear layer sheds off the slat cusp before it rolls up and forms several large-scale coherent structures. An evident train of vorticity structures along the slat shear layer ends on the slat cove surface, where strong vortex-body and vortex-vortex interactions occur. Flow reattachment of free shear layer vortex is identified for the potential broadband source mechanism. Comparative to vortex shedding from bluntness, it makes contribution to the low-frequency waves. As is generally agreed, slat noise is broadband in nature. Therefore, efforts in slat noise reduction must focus on the low-frequency broadband component. vortex shedding secondary separation vortex impingement edge scattering 3. Experimental design Figure 1: Slat noise source mechanisms. In this subsection, we introduce the test model and wind tunnel, then, discuss the new noise control method. 3.1 Configurations The test model is designed by Shanghai Aircraft Design and Research Institute design for slat noise research, as shown in figure 2. The airfoil takes cavity flow characteristics of 30P30N [7] for reference. Compared to three element airfoil, the two element airfoil is easier to be installed in wind tunnel, and has no trailing edge flap noise. Figure 2: Two dimensional airfoil. 3.2 Wind Tunnel The wind tunnel is a low speed wind tunnel of Nanjing University of Aeronautics and Astronautics, as shown in Figure 3. In this wind tunnel, a special wind tunnel controller (FSCG05/P05 CONVO) is designed, which is mainly used to provide a stable flow field for the aerodynamic test of various kinds of models. Open test section size: 0.8m (L) * 0.4m (W) * 0.6m (H). Motor power is less than 11KW. Adjusting the motor power, we can obtain the wind speed we expected in the 2 ICSV23, Athens (Greece), July 2016
3 test section. The wind uses soft connection between the wall of the wind tunnel and the motor so as to reduce the influence of the mechanical vibration of the motor. Figure 3: Wind tunnel. Aerodynamic noise research is generally carried out in an open wind tunnel, because the closed test section of the wall has a strong acoustic reflection and the sound insulation effect. The test model installation method is shown in Figure 4. The slat chord length is 0.088m and the slat span length is 0.6m. In the wind tunnel outlet, a collapsible organic glass plate is fixed to form a flow guiding plate. Figure 4: The installation mode of model. 3.3 Control methods The method of active vibration control is briefly described in figure 5. In figure 6, a slotted wall with two rows of piezoelectric fans are designed to replace aircraft skin, the location and dimension of the slot are also marked. Each piezoelectric fan is fabricated by bonding a piezoelectric patch to a shim material. The piezoelectric fan is simplified as a cantilever beam system.the idea behind the above method is to disturb the formation of shear layer by a local unsteady force, expecting a reduction of vortex impingement intensity on the slat cove surface. Figure 5: The control method. ICSV23, Athens (Greece), July
4 4. Results and Discussion Figure 6: The design of piezoelectric actuator. In this subsection, we discuss aerodynamic and aeroacoustic characteristics of baseline configuration, then, focus on the control effect of low noise configuration. 4.1 Aerodynamic aspects The flow field is measure by hot wire anemometer and oil flow. The hot wire is a precision measuring instrument, which can convert wind speed to electric signal, and then receive the wind speed value through the data collector. Velocity distribution in the cavity is obtained by measuring the velocity of each point in the slat cove by a hot wire velocity meter. The wind speed is 20m/s. The measurement method is shown in figure 7. Figure 7: Measurement using hot wire anemometer. The velocity image of slat cavity is the flow velocity of the intermediate XY plane. It is unable to measure the velocity distribution in the vicinity of the reattached area and the seam path. Figure 8 shows the experimental measurement of the velocity of the slat cavity. The interface between the low velocity zone and the external flow field is the free shear layer, the measurement by the hot wire identifies the approximate location of the shear layer. 4 ICSV23, Athens (Greece), July 2016
5 y[m] x[m] Figure 8: Velocity distribution of the cavity. The surface oil flow technique is applied to oil flow on the wall, it can visual the wall flow characteristics through the movement of the tracer particles in the coating. The wind speed is 20m/s. As shown in Figure 9, when the air impact the wall of the cavity wall, it leaves a white line, which is the reattachment point position. The distance between trailing edge and the reattachment point position is about 21mm Figure 9: Experimental results of oil flow. 4.2 Aeroacoustic aspects Sound intensity measurement has the advantages of strong anti-interference ability, and is not affected by the background noise. It is an effective method for noise source identification and sound field analysis. The test wind tunnel is a common low speed wind tunnel, not an acoustic wind tunnel. Environmental noise and background noise of wind tunnel are inevitable during the experiment, so the sound intensity method is chosen to measure the radiated noise. As shown in Figure 10, the sound intensity probe is located outside the wind tunnel test section, which is opposite to the point of attachment in the middle plane. The wind speed is 15m/s, 20m/s and 25m/s. The sampling frequency is 8192Hz, the sampling number is 4096, the resolution of frequency domain analysis is 2Hz. The linear average of each sample, the average number of times is 100 times. Figure 11: Sound intensity measurement. ICSV23, Athens (Greece), July
6 Figure 11 compares the point of the A with and without test model (wind tunnel background). It can be seen that the background noise decays from low frequency to high frequency, and the background noise is larger in the 20Hz~200Hz range. In this frequency band, the noise is submerged in the background noise, which can not be recognized. In the 200Hz~2000Hz range, the noise is much higher than the background noise of the wind tunnel. The noise obviously reduces with the increase of the frequency above 2000Hz. The results show that the 200Hz~2000Hz band is a low frequency broadband noise band, but it is difficult to be identified because of the interference of the measurement environment. PSD[dB/Hz] Frequency[Hz] without model with model 300Hz~2000Hz Figure 12: The sound intensity of point A with/without model. 4.3 Control effect The original model is defined as baseline configuration, the model is defined as low noise configuration after the installation of the actuator. Figure 12 compares the noise intensity results of the baseline configuration and the low noise configuration. As can be seen in the range of 200Hz~1500Hz, far field noise of low noise configuration declines about 10dB, which further illustrates shielding part recirculation zone can reduce the far field radiation noise of slat baseline configuration low noise configuration PSD[dB/Hz] Frequency[Hz] Figure 13: Sound intensity of baseline configuration and low noise configuration at point A. By applying a voltage of bimorph, we study the influence of actuator vibration on the slat noise. The reduction of point A is mainly concentrated in the fourth order (880Hz), and the other order of the peak is almost unchanged. It can be seen that the active control method can control the far field noise, but only reduces the fourth order, whose energy is relatively weak. 6 ICSV23, Athens (Greece), July 2016
7 Hz 600Hz PSD[dB/Hz] Frequency[Hz] Figure 14: Control effect. 5. Conclusions An active vibration control method applied to slat noise reduction is studied in this paper. The introduction of the vibrational surface changes the configuration. The deformation of the vibrational surface is very small, but it changes the shear layer stemming from the cusp. The results, achieved by experiment, show a 4 db reduction of farfield noise. Current works have verified the effectiveness of the active vibration control. Further work will concern on the concept of optimum parameters. REFERENCES 1 Dobrzynski W. Almost 40 years of airframe noise research: What did we achieve? Journal of aircraft, 47(2): , (2010). 2 Choudhari M M, Lockard D P, Macaraeg M G, et al. NASA/TM , Aeroacoustic experiments in the Langley low-turbulence pressure tunnel, (2002). 3 Takeda, K., Zhang, X., & Nelson, P. A. Unsteady aerodynamics and aeroacoustics of a high-lift device configuration, 40 th AIAA Aerospace Sciences Meeting & Exhibit, Reno, NV, U.S.A., (2002). 4 Olson, S., Thomas, F., & Nelson, R. Mechanisms of slat noise production in a 2D multi-element airfoil configuration, 7 th AIAA/CEAS Aeroacoustics Conference and Exhibit. Maastricht, Netherlands, (2001) 5 Mendoza, J. M., Brooks, T. F., & Humphreys, W. Aeroacoustic measurements of a wing/slat model, 8 th AIAA/CEAS Aeroacoustics Conference & Exhibit. Breckenridge, CO U.S.A., June, (2002) 6 Choudhari, M. M., & Khorrami, M. R. Effect of three-dimensional shear-layer structures on slat cove unsteadiness. AIAA journal, 45(9), , (2007). 7 Klausmeyer S M, Lin J C. Comparative results from a CFD challenge over a 2D three-element high-lift airfoil. National Aeronautics and Space Administration, Langley Research Center, (1997). ICSV23, Athens (Greece), July
Experimental study of broadband trailing edge noise of a linear cascade and its reduction with passive devices
PhD Defense Experimental study of broadband trailing edge noise of a linear cascade and its reduction with passive devices Arthur Finez LMFA/École Centrale de Lyon Thursday 1 th May 212 A. Finez (LMFA/ECL)
More informationTHE high level of nuisance noise generated by the take-off and landing of aircraft has a significant impact on the communities
Bluff Body Noise and Flow Control with Atmospheric Plasma Actuators Xun Huang Xin Zhang and Steve Gabriel University of Southampton, Southampton, SO7 BJ, United Kingdom Plasma actuators operating in atmospheric
More informationEXPERIMENTAL STUDY OF THE MORPHING FLAP AS A LOW NOISE HIGH LIFT DEVICE FOR AIRCRAFT WING
28 TH INTERNATIONAL CONGRESS OF THE AERONAUTICAL SCIENCES EXPERIMENTAL STUDY OF THE MORPHING FLAP AS A LOW NOISE HIGH LIFT DEVICE FOR AIRCRAFT WING Yasuhiro TANI*, Yoshiyuki MATSUDA*, Akira DOI*, Yuya
More informationOverview of Turbofan Engine Noise
Overview of Turbofan Engine Noise Oksana Stalnov Faculty of Aerospace Engineering Technion Israel Institute of Technology Some statistics Current aircraft are 20-30 db quieter than first generation turbofans
More informationEffects of Angle of Attack and Velocity on Trailing Edge Noise
42 nd AIA Aerospace Sciences Meeting, Reno, NV, January 5-8, 2004 AIAA-2004-1031 Effects of Angle of Attack and Velocity on Trailing Edge Noise Florence V. Hutcheson* Thomas F. Brooks NASA Langley Research
More informationEFFECTS OF PHYSICAL CONFIGURATIONS ON ANC HEADPHONE PERFORMANCE
EFFECTS OF PHYSICAL CONFIGURATIONS ON ANC HEADPHONE PERFORMANCE Lifu Wu Nanjing University of Information Science and Technology, School of Electronic & Information Engineering, CICAEET, Nanjing, 210044,
More informationExperimental Investigation of Unsteady Pressure on an Axial Compressor Rotor Blade Surface
Energy and Power Engineering, 2010, 2, 131-136 doi:10.4236/epe.2010.22019 Published Online May 2010 (http://www. SciRP.org/journal/epe) 131 Experimental Investigation of Unsteady Pressure on an Axial Compressor
More informationEXPERIMENTS ON PERFORMANCES OF ACTIVE-PASSIVE HYBRID MUFFLERS
EXPERIMENTS ON PERFORMANCES OF ACTIVE-PASSIVE HYBRID MUFFLERS Hongling Sun, Fengyan An, Ming Wu and Jun Yang Key Laboratory of Noise and Vibration Research, Institute of Acoustics, Chinese Academy of Sciences,
More informationFLOW INDUCED NOISE CONSIDERATIONS FOR THE WIND TUNNEL TESTING OF A NACA 0015 AIRFOIL WITH SLOTS
FLOW INDUCED NOISE CONSIDERATIONS FOR THE WIND TUNNEL TESTING OF A NACA 0015 AIRFOIL WITH SLOTS Robert Bruce Alstrom, Pier Marzocca, Goodarz Ahmadi Department of Mechanical and Aeronautical Engineering
More informationANALYTICAL NOISE MODELLING OF A CENTRIFUGAL FAN VALIDATED BY EXPERIMENTAL DATA
ANALYTICAL NOISE MODELLING OF A CENTRIFUGAL FAN VALIDATED BY EXPERIMENTAL DATA Beatrice Faverjon 1, Con Doolan 1, Danielle Moreau 1, Paul Croaker 1 and Nathan Kinkaid 1 1 School of Mechanical and Manufacturing
More informationINFLUENCE OF CAPTIVE STORES ON THE UNSTEADY PRESSURE DISTRIBUTION WITHIN A RECTANGULAR CAVITY
25 TH INTERNATIONAL CONGRESS OF THE AEROSPACE SCIENCES INFLUENCE OF CAPTIVE STORES ON THE UNSTEADY PRESSURE DISTRIBUTION WITHIN A RECTANGULAR CAVITY D.M. Orchard, B.H.K. Lee and F.C. Tang Aerodynamics
More informationInfluence of SDBD plasma aerodynamic actuation on flow control by AC power supply and AC-DC power supply
IOP Conference Series: Earth and Environmental Science PAPER OPEN ACCESS Influence of SDBD plasma aerodynamic actuation on flow control by AC power supply and AC-DC power supply To cite this article: Xu
More informationARRAY SHADING APPLIED TO BEAMFORMING TECHNIQUE FOR EVALUATION OF SLAT NOISE FROM 6 TO 18 ANGLES OF ATTACK
Proceedings of EPTT 16 Copyright c 16 ABCM 1th ABCM Spring School on Transition and Turbulence ARRAY SHADING APPLIED TO BEAMFORMING TECHNIQUE FOR EVALUATION OF SLAT NOISE FROM 6 TO 18 ANGLES OF ATTACK
More informationDiagnosing Interior Noise due to Exterior Flows in STAR-CCM+ Phil Shorter, CD-adapco
Diagnosing Interior Noise due to Exterior Flows in STAR-CCM+ Phil Shorter, CD-adapco Overview Problem of interest Analysis process Modeling direct field acoustic radiation from a panel Direct fields for
More informationACTIVE FLOW CONTROL USING HIGH FREQUENCY COMPLIANT STRUCTURES
c)2001 American Institute of Aeronautics & Astronautics or Published with Permission of Author(s) and/or Author(s)' Sponsoring Organization. A01-37346 ACTIVE FLOW CONTROL USING HIGH FREQUENCY COMPLIANT
More informationPanPhonics Panels in Active Control of Sound
PanPhonics White Paper PanPhonics Panels in Active Control of Sound Seppo Uosukainen VTT Building and Transport Contents Introduction... 1 Active control of sound... 1 Interference... 2 Control system...
More informationMICROPHONE ARRAY MEASUREMENTS ON AEROACOUSTIC SOURCES
MICROPHONE ARRAY MEASUREMENTS ON AEROACOUSTIC SOURCES Andreas Zeibig 1, Christian Schulze 2,3, Ennes Sarradj 2 und Michael Beitelschmidt 1 1 TU Dresden, Institut für Bahnfahrzeuge und Bahntechnik, Fakultät
More informationAeroacoustic Experiments in the Langley Low-Turbulence Pressure Tunnel
NASA/TM-2002-211432 Aeroacoustic Experiments in the Langley Low-Turbulence Pressure Tunnel Meelan M. Choudhari, David P. Lockard, Michele G. Macaraeg, Bart A. Singer, and Craig L. Streett Langley Research
More informationCHARACTERISTICS OF AERODYNAMIC NOISE FROM THE INTER-COACH SPACING OF A HIGH-SPEED TRAIN. Woulam-dong, Uiwang-city, Gyunggi-do, Korea,
ICSV14 Cairns Australia 9-12 July, 2007 CHARACTERISTICS OF AERODYNAMIC NOISE FROM THE INTER-COACH SPACING OF A HIGH-SPEED TRAIN Sunghoon Choi 1, Hyoin Koh 1, Chan-Kyung Park 1, and Junhong Park 2 1 Korea
More informationFOREBODY VORTEX CONTROL ON HIGH PERFORMANCE AIRCRAFT USING PWM- CONTROLLED PLASMA ACTUATORS
26 TH INTERNATIONAL CONGRESS OF THE AERONAUTICAL SCIENCES FOREBODY VORTEX CONTROL ON HIGH PERFORMANCE AIRCRAFT USING PWM- CONTROLLED PLASMA ACTUATORS Takashi Matsuno*, Hiromitsu Kawazoe*, Robert C. Nelson**,
More informationEffect of Flow Impingement on the Acoustic Resonance Excitation in A Shallow Rectangular Cavity
Effect of Flow Impingement on the Acoustic Resonance Excitation in A Shallow Rectangular Cavity Ahmed Omer 1), Atef Mohany 2) * and Marwan Hassan 3) 1),2) University of Ontario Institute of Technology,
More informationTHE INFLUENCE OF MODULATED SLOTTED SYNTHETIC JET ON THE BYPASS OF HUMP
Engineering MECHANICS, Vol. 20, 2013, No. 3/4, p. 271 280 271 THE INFLUENCE OF MODULATED SLOTTED SYNTHETIC JET ON THE BYPASS OF HUMP Petr Pick*, Miroslav Andrle*, Vladislav Skála*, Milan Matějka* The articles
More informationAPPLICATION OF PHASED ARRAY IN THE STUDY OF LINEAR CASCADE NOISE REDUCTION ON THE INDOOR TEST BED
BeBeC-2014-22 APPLICATION OF PHASED ARRAY IN THE STUDY OF LINEAR CASCADE NOISE REDUCTION ON THE INDOOR TEST BED Weiyang Qiao 1, Liang Ji 2, Fan Tong 3, Kunbo Xu 4, and Weijie Chen 5 School of Power and
More informationACOUSTIC WIND TUNNEL MEASUREMENTS ON A LIVE LEVEL FLIGHT PIGEON
BeBeC-2014-25 ACOUSTIC WIND TUNNEL MEASUREMENTS ON A LIVE LEVEL FLIGHT PIGEON Qingkai Wei 1, Wenjun Yu 1 and Xun Huang 1,2 1 Department of Aeronautics and Astronautics, College of Engineering, Peking University.
More informationLANDING a helicopter on to the flight deck of a ship can be a formidable task for even the most
Aerodynamic Evaluation of Ship Geometries using CFD and Piloted Helicopter Flight Simulation James S. Forrest, Ieuan Owen and Christopher H. Kääriä Department of Engineering University of Liverpool, Brownlow
More information1. Introduction The presence of a cavity changes the mean and fluctuating pressure distributions inside and near a cavity [1,2].
1. Introduction The presence of a cavity changes the mean and fluctuating pressure distributions inside and near a cavity [1,2]. For compressible flow in a rectangular cavity (M = 0.95), the mean and fluctuation
More informationAIAA Model-Based Control of Cavity Oscillations Part 1: Experiments D.R. Williams Illinois Institute of Technology, Chicago IL C.
AIAA 22-971 Model-Based Control of Cavity Oscillations Part 1: Experiments D.R. Williams Illinois Institute of Technology, Chicago IL C. Rowley Princeton University, Princeton NJ T. Colonius, R. Murray,
More information8th AIAA/CEAS Aeroacoustics Conference June 16 18, 2002/Breckenridge, CO
AIAA 22-2416 Noise Transmission Characteristics of Damped Plexiglas Windows Gary P. Gibbs, Ralph D. Buehrle, Jacob Klos, Sherilyn A. Brown NASA Langley Research Center, Hampton, VA 23681 8th AIAA/CEAS
More informationApplication of Artificial Neural Network for the Prediction of Aerodynamic Coefficients of a Plunging Airfoil
International Journal of Science and Engineering Investigations vol 1, issue 1, February 212 Application of Artificial Neural Network for the Prediction of Aerodynamic Coefficients of a Plunging Airfoil
More informationFrom (CTS) wind tunnel data to noise impact assessment
From (CTS) wind tunnel data to noise impact assessment Mark-Jan van der Meulen, Harry Brouwer, Marthijn Tuinstra & Kylie Knepper CEAS-ASC workshop 2018 Introduction Current best practice: Aerodynamic test
More informationACTIVE CONTROL USING MOVING BOTTOM WALL APPLIED TO OPEN CAVITY SELF-SUSTAINED OSCILLATION WITH MODE SWITCHING
6th European Conference on Computational Mechanics (ECCM 6) 7th European Conference on Computational Fluid Dynamics (ECFD 7) 11 15 June 2018, Glasgow, UK ACTIVE CONTROL USING MOVING BOTTOM WALL APPLIED
More informationINFLUENCE OF MEMBRANE AMPLITUDE AND FORCING FREQUENCY ON SYNTHETIC JET VELOCITY
TASKQUARTERLYvol.19,No2,2015,pp.111 120 INFLUENCE OF MEMBRANE AMPLITUDE AND FORCING FREQUENCY ON SYNTHETIC JET VELOCITY MARCIN KUROWSKI AND PIOTR DOERFFER Institute of Fluid-Flow Machinery, Polish Academy
More informationWIND-INDUCED VIBRATION OF SLENDER STRUCTURES WITH TAPERED CIRCULAR CYLINDERS
The Seventh Asia-Pacific Conference on Wind Engineering, November 8-2, 2009, Taipei, Taiwan WIND-INDUCED VIBRATION OF SLENDER STRUCTURES WITH TAPERED CIRCULAR CYLINDERS Delong Zuo Assistant Professor,
More informationThe Effects of Sweeping Jet Actuator Parameters on Flow Separation Control
https://ntrs.nasa.gov/search.jsp?r=20160006025 2019-01-08T00:14:38+00:00Z The Effects of Sweeping Jet Actuator Parameters on Flow Separation Control Mehti Koklu 1 NASA Langley Research Center, Hampton,
More informationACTIVE FLOW CONTROL TECHNIQUE USING PIEZO-FILM ACTUATORS APPLIED TO THE SOUND GENERATION BY A CAVITY. X : location in the streamwise direction
Proceedings of the 3rd ASMENSME Joint Fluids Engineering Cbnference July 18-23,1999, San Francisco, California FEDSM99-7232 ACIVE FLOW CONROL ECHNIQUE USING PIEZO-FILM ACUAORS APPLIED O HE SOUND GENERAION
More informationNASA Contractor Report K. K. Ahuja and J. Mendoza Georgia Institute of Technology Atlanta, Georgia
NASA Contractor Report 4653 Effects of Cavity Dimensions, Boundary Layer, and Temperature on Cavity Noise With Emphasis on Benchmark Data To Validate Computational Aeroacoustic Codes K. K. Ahuja and J.
More informationF-16 Quadratic LCO Identification
Chapter 4 F-16 Quadratic LCO Identification The store configuration of an F-16 influences the flight conditions at which limit cycle oscillations develop. Reduced-order modeling of the wing/store system
More informationDEVELOPMENT OF AN ACOUSTIC MEASUREMENT CAPABILITY FOR AUTOMOTIVE TESTING IN OPEN-JET WIND TUNNELS
DEVELOPMENT OF AN ACOUSTIC MEASUREMENT CAPABILITY FOR AUTOMOTIVE TESTING IN OPEN-JET WIND TUNNELS Author: Brianne Y. Williams Advisor: Dr. Colin P. Britcher Old Dominion University, Norfolk, VA. 359 Automobile
More informationCONTROL LAW SYNTHESIS FOR VERTICAL FIN BUFFETING ALLEVIATION USING STRAIN ACTUATION
AIAA 99-1317 CONTROL LAW SYNTHESIS FOR VERTICAL FIN BUFFETIN ALLEVIATION USIN STRAIN ACTUATION F. Nitzsche * and D.. Zimcik National Research Council of Canada Institute for Aerospace Research Ottawa,
More informationPASSIVE CONTROL OF CAVITY INSTABILITIES AND NOISE
27 TH INTERNATIONAL CONGRESS OF THE AERONAUTICAL SCIENCES PASSIVE CONTROL OF CAVITY INSTABILITIES AND NOISE K Knowles, B Khanal, D Bray, P Geraldes Aeromechanical Systems Group, Cranfield University Defence
More informationFlow-induced vibration in the compressible cavity flow
Flow-induced vibration in the compressible cavity flow Hao Li 1, Jianguo Tan 2, Juwei Hou 3 Science and Technology on Scramjet Laboratory, National University of Defense Technology, Changsha, Hunan Province,
More informationNoise from Pulsating Supercavities Prepared by:
Noise from Pulsating Supercavities Prepared by: Timothy A. Brungart Samuel E. Hansford Jules W. Lindau Michael J. Moeny Grant M. Skidmore Applied Research Laboratory The Pennsylvania State University Flow
More informationDesign and Calibration of a Small Aeroacoustic Beamformer
Proceedings of 20 th International Congress on Acoustics, ICA 2010 23-27 August 2010, Sydney, Australia Design and Calibration of a Small Aeroacoustic Beamformer Elias J. G. Arcondoulis, Con J. Doolan,
More informationA Method for Estimating Noise from Full-Scale Distributed Exhaust Nozzles
A Method for Estimating Noise from Full-Scale Distributed Exhaust Nozzles Kevin W. Kinzie * NASA Langley Research Center, Hampton, VA 23681 David. B. Schein Northrop Grumman Integrated Systems, El Segundo,
More informationNASA Langley Activities on Broadband Fan Noise Reduction via Novel Liner Technologies
NASA Langley Activities on Broadband Fan Noise Reduction via Novel Liner Technologies Michael G. Jones NASA Langley Research Center, Hampton, VA CEAS/X-Noise Workshop on Broadband Noise of Rotors and Airframe
More informationExperimental Closed Loop Control of Flow Separation on a Simple Hinged Flap
Experimental Closed Loop Control of Flow Separation on a Simple Hinged Flap T. Chabert1, J. Dandois1, E. Garnier1 and L. Jacquin2 Onera, The French Aerospace Lab, Applied Aerodynamics Department 2 Fundamental
More informationPREDICTION OF SUPERCOOLED DROPLET IMPINGEMENT ON HELICOPTER ROTOR BLADES
26 TH INTERNATIONAL CONGRESS OF THE AERONAUTICAL SCIENCES PREDICTION OF SUPERCOOLED DROPLET IMPINGEMENT ON HELICOPTER ROTOR BLADES Krzysztof Szilder, Hongyi Xu Institute for Aerospace Research, National
More informationEDITORIAL NEWSLETTER WINTER 2009/2010. Dear colleague,
http://www.xnoise.eu EDITORIAL NEWSLETTER WINTER 2009/2010 Dear colleague, Contents Welcome to our third newsletter. Please forward to your colleagues to encourage their participation in the X3-Noise Network
More informationACTIVE LOW-FREQUENCY MODAL NOISE CANCELLA- TION FOR ROOM ACOUSTICS: AN EXPERIMENTAL STUDY
ACTIVE LOW-FREQUENCY MODAL NOISE CANCELLA- TION FOR ROOM ACOUSTICS: AN EXPERIMENTAL STUDY Xavier Falourd, Hervé Lissek Laboratoire d Electromagnétisme et d Acoustique, Ecole Polytechnique Fédérale de Lausanne,
More informationAn investigation of the fluid-structure interaction in an oscillating-wing micro-hydropower generator
An investigation of the fluid-structure interaction in an oscillating-wing micro-hydropower generator K.D. Jones, K. Lindsey & M.F. Platzer Department of Aeronautics & Astronautics, Naval Postgraduate
More information3D Tip Flow Characteristics and Vortex Shedding from a Radar Antenna used for Airport Ground Traffic Control
ISROMAC-11 Proceedings of the International Symposium on Transport Phenomena and Dynamics of Rotating Machinery, Feb.26-March 2, 2006, Honolulu, Hawaii, USA 3D Tip Flow Characteristics and Vortex Shedding
More informationTOWARDS PRECISE PREDICTION OF FLOW PATTERS OF RESONATORS UNDER GRAZING FLOWS BY USING CARTESIAN- MESH CFD
6th European Conference on Computational Mechanics (ECCM 6) 7th European Conference on Computational Fluid Dynamics (ECFD 7) 11 15 June 2018, Glasgow, UK TOWARDS PRECISE PREDICTION OF FLOW PATTERS OF RESONATORS
More informationTAU Experiences with Detached-Eddy Simulations
TAU Experiences with Detached-Eddy Simulations Herbert Rieger & Stefan Leicher EADS Deutschland GmbH Military Aircraft Flight Physics Department Ottobrunn, Germany Outline The Typical Design Problem of
More informationSimple Feedback Structure of Active Noise Control in a Duct
Strojniški vestnik - Journal of Mechanical Engineering 54(28)1, 649-654 Paper received: 6.9.27 UDC 534.83 Paper accepted: 7.7.28 Simple Feedback Structure of Active Noise Control in a Duct Jan Černetič
More informationACTIVE CONTROL OF AUTOMOBILE CABIN NOISE WITH CONVENTIONAL AND ADVANCED SPEAKERS. by Jerome Couche
ACTIVE CONTROL OF AUTOMOBILE CABIN NOISE WITH CONVENTIONAL AND ADVANCED SPEAKERS by Jerome Couche Thesis submitted to the Faculty of the Virginia Polytechnic Institute and State University in partial fulfillment
More informationUniversity of Bath. DOI: /s Publication date: Document Version Peer reviewed version. Link to publication
Citation for published version: Hu, T, Wang, Z & Gursul, I 2014, 'Passive control of roll oscillations of low-aspect-ratio wings using bleed' Experiments in Fluids, vol. 55, 1752. https://doi.org/10.1007/s00348-014-1752-2
More informationImplementation of decentralized active control of power transformer noise
Implementation of decentralized active control of power transformer noise P. Micheau, E. Leboucher, A. Berry G.A.U.S., Université de Sherbrooke, 25 boulevard de l Université,J1K 2R1, Québec, Canada Philippe.micheau@gme.usherb.ca
More informationNASA Fundamental Aeronautics Program Jay Dryer Director, Fundamental Aeronautics Program Aeronautics Research Mission Directorate
National Aeronautics and Space Administration NASA Fundamental Aeronautics Program Jay Dryer Director, Fundamental Aeronautics Program Aeronautics Research Mission Directorate www.nasa.gov July 2012 NASA
More informationAEROACOUSTIC NOISE MEASUREMENTS IN AERODYNAMIC LOW-SPEED WIND TUNNELS
26 TH INTERNATIONAL CONGRESS OF THE AERONAUTICAL SCIENCES AEROACOUSTIC NOISE MEASUREMENTS IN AERODYNAMIC LOW-SPEED WIND TUNNELS Takeshi ITO*, Hiroki URA*, Yuzuru YOKOKAWA* * Japan Aerospace Exploration
More informationUNSTEADINESS OF BLADE-PASSING FREQUENCY TONES OF AXIAL FANS
The 1 st International Congress on Sound and Vibration 13-17 July, 014, Beijing/China UNSTEADINESS OF BLADE-PASSING FREQUENCY TONES OF AXIAL FANS Michael Sturm, Thomas Carolus Institute of Fluid- and Thermodynamics,
More informationA New Lamb-Wave Based NDT System for Detection and Identification of Defects in Composites
SINCE2013 Singapore International NDT Conference & Exhibition 2013, 19-20 July 2013 A New Lamb-Wave Based NDT System for Detection and Identification of Defects in Composites Wei LIN, Lay Siong GOH, B.
More informationStudy on the Lift-off Effect of EMAT
17th World Conference on Nondestructive Testing, 25-28 Oct 2008, Shanghai, China Study on the Lift-off Effect of EMAT Yongsheng ZANG, Songling UANG, Wei ZAO, Shen WWANG, Dehui WU State Key Lab of Power
More informationCFD Study of Cavity Flows. D. Lawrie, P. Nayyar K. Badcock, G. Barakos and B. Richards
CFD Study of Cavity Flows D. Lawrie,. Nayyar K. Badcock, G. Barakos and B. Richards CFD Laboratory Department Of Aerospace Engineering University of Glasgow Glasgow G12 8QQ UK www.aero.gla.ac.uk/research/cfd
More informationNoise Attenuation by Two One Degree of Freedom Helmholtz Resonators
Global Science and Technology Journal Vol. 3. No. 1. March 015 Issue. Pp.1-9 Noise Attenuation by Two One Degree of Freedom Helmholtz Resonators Md. Amin Mahmud a*, Md. Zahid Hossain b, Md. Shahriar Islam
More informationThe Active Flutter Suppression (AFS) Technology Evaluation Project
1 The Active Flutter Suppression (AFS) Technology Evaluation Project Eli Livne, Ph.D. The William E. Boeing Department of Aeronautics and Astronautics University of Washington, Seattle, WA eli@aa.washington.edu
More informationNoise source characterization by highfrequency surface pressure measurements
Noise source characterization by highfrequency surface pressure measurements Helge Aagaard Madsen Andreas Fischer Franck Bertagnolio Christian Bak Section Aeroelastic Design Department of Wind Energy hama@dtu.dk
More informationThe Research on Application of Cadna/A Software in Noise Prediction of Urban Substation
2016 3 rd International Conference on Engineering Technology and Application (ICETA 2016) ISBN: 978-1-60595-383-0 The Research on Application of Cadna/A Software in Noise Prediction of Urban Substation
More informationCOMBINING SIGNAL PRE-PROCESSING METHODS WITH BEAMFORMING FOR BROADBAND TURBOMACHINERY APPLICATIONS
BeBeC-2018-D28 COMBINING SIGNAL PRE-PROCESSING METHODS WITH BEAMFORMING FOR BROADBAND TURBOMACHINERY APPLICATIONS Kristóf Tokaji and Csaba Horváth Department of Fluid Mechanics, Faculty of Mechanical Engineering
More informationA Hybrid Trailing Edge Control Surface Concept
Pınar ARSLAN, Uğur KALKAN, Harun TIRAŞ, İlhan Ozan TUNÇÖZ, Yosheph YANG, Ercan GÜRSES, Melin ŞAHİN, Serkan ÖZGEN, Yavuz YAMAN Department of Aerospace Enginnering, Middle East Technical University Ankara,
More informationOn the Development of Semi-Empirical Noise Models for the Prediction of the Noise from Jets with Forced Mixers
10th AIAA/CEAS Aeroacoustics Conference AIAA 2004-2898 On the Development of Semi-Empirical Noise Models for the Prediction of the Noise from Jets with Forced Mixers L. A. Garrison * Purdue University,
More informationUAV Flight Control Using Flow Control Actuators
AIAA Atmospheric Flight Mechanics Conference 08-11 August 2011, Portland, Oregon AIAA 2011-6450 UAV Flight Control Using Flow Control Actuators Eric N Johnson, Girish Chowdhary, Rajeev Chandramohan, Anthony
More informationALLEGRA Project ADVANCED LOW NOISE LANDING (MAIN
ALLEGRA Project ADVANCED LOW NOISE LANDING (MAIN AND NOSE) GEAR FOR REGIONAL AIRCRAFT GRANT AGREEMENT NO: 308225 ALLEGRA Consortium www.cleansky.eu EUROTECH s EUROTECH s.a.s. Project Overview Call SP1-JTI-CS-2011-03
More informationLOCALIZATION OF WIND TURBINE NOISE SOURCES USING A COMPACT MICROPHONE ARRAY WITH ADVANCED BEAMFORMING ALGORITHMS
BeBeC-2012-25 LOCALIZATION OF WIND TURBINE NOISE SOURCES USING A COMPACT MICROPHONE ARRAY WITH ADVANCED BEAMFORMING ALGORITHMS Rakesh C. Ramachandran, Hirenkumar Patel and Ganesh Raman Fluid Dynamic Research
More informationUltrasonic Guided Wave Applications
Ultrasonic Guided Wave Applications Joseph L. Rose Penn State University April 29-30, 2013 2013 Center for Acoustics and Vibrations meeting What is a Guided Wave? (Guided wave requires boundary for propagation
More informationAirflow visualization in a model of human glottis near the self-oscillating vocal folds model
Applied and Computational Mechanics 5 (2011) 21 28 Airflow visualization in a model of human glottis near the self-oscillating vocal folds model J. Horáček a,, V. Uruba a,v.radolf a, J. Veselý a,v.bula
More informationMulti-channel Active Control of Axial Cooling Fan Noise
The 2002 International Congress and Exposition on Noise Control Engineering Dearborn, MI, USA. August 19-21, 2002 Multi-channel Active Control of Axial Cooling Fan Noise Kent L. Gee and Scott D. Sommerfeldt
More informationComposite aeroacoustic beamforming of an axial fan
Acoustics Array Systems: Paper ICA2016-122 Composite aeroacoustic beamforming of an axial fan Jeoffrey Fischer (a), Con Doolan (b) (a) School of Mechanical and Manufacturing Engineering, UNSW Australia,
More informationSource Control of Turbomachine Discrete- Frequency Tone Generation
Purdue e-pubs International Compressor Engineering Conference School of Mechanical Engineering 1996 Source Control of Turbomachine Discrete- Frequency Tone Generation S. Sawyer S. Fleeter Follow this and
More information1681. Omni-directional damage detection and localization with a cruciform piezoelectric ultrasonic phased array
1681. Omni-directional damage detection and localization with a cruciform piezoelectric ultrasonic phased array Zhiling Wang 1, Shenfang Yuan, Lei Qiu 3, Bin Liu 4 1,, 3, 4 The State Key Laboratory of
More informationINTRODUCTION. Reducing noise annoyance. Aircraft noise is a global problem. First, we have to know how sound is emitted and propagated
R E S E A R C H INTRODUCTION Reducing noise annoyance Aircraft noise is a global problem Aircraft play active roles in various fields, including passenger transportation, physical distribution, and disaster
More informationMEASUREMENT OF SURFACE ACOUSTIC WAVE USING AIR COUPLED TRANSDUCER AND LASER DOPPLER VIBROMETER
21 st International Conference on Composite Materials Xi an, 20-25 th August 2017 MEASUREMENT OF SURFACE ACOUSTIC WAVE USING AIR COUPLED TRANSDUCER AND LASER DOPPLER VIBROMETER Weitao Yuan 1, Jinfeng Zhao
More informationCOMPACT WIDE-SLOT TRI-BAND ANTENNA FOR WLAN/WIMAX APPLICATIONS
Progress In Electromagnetics Research Letters, Vol. 18, 9 18, 2010 COMPACT WIDE-SLOT TRI-BAND ANTENNA FOR WLAN/WIMAX APPLICATIONS Q. Zhao, S. X. Gong, W. Jiang, B. Yang, and J. Xie National Laboratory
More informationFLUTTER CONTROL OF WIND TUNNEL MODEL USING A SINGLE ELEMENT OF PIEZO-CERAMIC ACTUATOR
24 TH INTERNATIONAL CONGRESS OF THE AERONAUTICAL SCIENCES FLUTTER CONTROL OF WIND TUNNEL MODEL USING A SINGLE ELEMENT OF PIEZO-CERAMIC ACTUATOR Naoki Kawai Department of Mechanical Engineering, University
More informationSLAT NOISE ASSESSMENT FROM A340 FLYOVER ACOUSTIC MEASUREMENTS WITH A MICROPHONE PHASED ARRAY 4 TH BERLIN BEAMFORMING CONFERENCE
BeBeC-2012-02 SLAT NOISE ASSESSMENT FROM A340 FLYOVER ACOUSTIC MEASUREMENTS WITH A MICROPHONE PHASED ARRAY 4 TH BERLIN BEAMFORMING CONFERENCE Vincent Fleury and Patrice Malbéqui Onera 29 avenue de la Division
More informationUNSTEADY AERODYNAMIC INFORMATION EXTRACTION USING FFT-BASED UNSTEADY PRESSURE-SENSITIVE PAINT MEASUREMENT
UNSTEADY AERODYNAMIC INFORMATION EXTRACTION USING FFT-BASED UNSTEADY PRESSURE-SENSITIVE PAINT MEASUREMENT Kazuyuki Nakakita* * Japan Aerospace Exploration Agency Keywords: Unsteady Aerodynamics, Pressure-Sensitive
More informationBearing fault detection of wind turbine using vibration and SPM
Bearing fault detection of wind turbine using vibration and SPM Ruifeng Yang 1, Jianshe Kang 2 Mechanical Engineering College, Shijiazhuang, China 1 Corresponding author E-mail: 1 rfyangphm@163.com, 2
More informationUltrasonic Infrared Thermal Wave Technology and Its Applications in. Nondestructive Evaluation
17th World Conference on Nondestructive Testing, 25-28 Oct 2008, Shanghai, China Ultrasonic Infrared Thermal Wave Technology and Its Applications in Nondestructive Evaluation Dapeng CHEN, Cunlin ZHANG,
More informationENHANCEMENT OF THE TRANSMISSION LOSS OF DOUBLE PANELS BY MEANS OF ACTIVELY CONTROLLING THE CAVITY SOUND FIELD
ENHANCEMENT OF THE TRANSMISSION LOSS OF DOUBLE PANELS BY MEANS OF ACTIVELY CONTROLLING THE CAVITY SOUND FIELD André Jakob, Michael Möser Technische Universität Berlin, Institut für Technische Akustik,
More informationUniversity of Bath. Publication date: Document Version Peer reviewed version. Link to publication
Citation for published version: Hu, T, Wang, Z & Gursul, I 2014, 'Passive control of self-induced roll oscillations using bleed' Paper presented at 52nd AIAA Aerospace Sciences Meeting - AIAA Science and
More informationPhased Array Aeroacoustic Measurements of an Unmanned Aerial Vehicle
Phased Array Aeroacoustic Measurements of an Unmanned Aerial Vehicle Alessandro DI MARCO 1 ; Lorenzo BURGHIGNOLI 1 ; Francesco CENTRACCHIO 1 ; Roberto CAMUSSI 1 ; Thomas AHLEFELDT 2 ; Arne HENNING 2 ;
More informationSTRUCTURAL AND ACOUSTIC NUMERICAL MODELING OF A CURVED COMPOSITE HONEYCOMB PANEL
AIAA-2001-2277 STRUCTURAL AND ACOUSTIC NUMERICAL MODELING OF A CURVED COMPOSITE HONEYCOMB PANEL Ferdinand W. Grosveld* Lockheed Martin Engineering and Sciences Hampton, VA 23681 Ralph D. Buehrle and Jay
More informationYour title goes here. Aeroacoustics. Methodologies, Validations and Continuing Outlook
Your title goes here Aeroacoustics Methodologies, Validations and Continuing Outlook Your subtitle goes here Fred Mendonça Some Characteristic Flow Noise Issues Automotive external, sunroof buffeting,
More informationEXPERIMENTAL AND NUMERICAL STUDY OF AN AUTONOMOUS FLAP
EXPERIMENTAL AND NUMERICAL STUDY OF AN AUTONOMOUS FLAP Lars O. Bernhammer 1, Sachin T. Navalkar 1, Jurij Sodja 1, Roeland De Breuker 1, Moti Karpel 2 1 Delft University of Technology Delft, 2629HS, The
More informationResearch Article A Wide-Bandwidth Monopolar Patch Antenna with Dual-Ring Couplers
Antennas and Propagation, Article ID 9812, 6 pages http://dx.doi.org/1.1155/214/9812 Research Article A Wide-Bandwidth Monopolar Patch Antenna with Dual-Ring Couplers Yuanyuan Zhang, 1,2 Juhua Liu, 1,2
More informationA COMPACT MULTIBAND MONOPOLE ANTENNA FOR WLAN/WIMAX APPLICATIONS
Progress In Electromagnetics Research Letters, Vol. 23, 147 155, 2011 A COMPACT MULTIBAND MONOPOLE ANTENNA FOR WLAN/WIMAX APPLICATIONS Z.-N. Song, Y. Ding, and K. Huang National Key Laboratory of Antennas
More informationMicrophone Array Measurements for High-speed Train
Microphone Array Measurements for High-speed Train Korea Research Institute of Standards and Science Hyu-Sang Kwon 2016. 05. 31 2 Contents Railway Noise Sound Images Flow Noise Railway Noise Measurement
More informationInvestigation of Noise Spectrum Characteristics for an Evaluation of Railway Noise Barriers
IJR International Journal of Railway Vol. 6, No. 3 / September 2013, pp. 125-130 ISSN 1976-9067(Print) ISSN 2288-3010(Online) Investigation of Noise Spectrum Characteristics for an Evaluation of Railway
More informationPenn State University ESM Ultrasonics R&D Laboratory Joseph L. Rose Research Activities
Penn State University ESM Ultrasonics R&D Laboratory Joseph L. Rose Research Activities Crack Detection in Green Compacts The Center for Innovative Sintered Products Identifying cracked green parts before
More informationStatistical analysis of nonlinearly propagating acoustic noise in a tube
Statistical analysis of nonlinearly propagating acoustic noise in a tube Michael B. Muhlestein and Kent L. Gee Brigham Young University, Provo, Utah 84602 Acoustic fields radiated from intense, turbulent
More informationSource localisation on aircraft in flight - new measurements with the DLR research aircraft Airbus 320 ATRA
BeBeC-2018-D01 Source localisation on aircraft in flight - new measurements with the DLR research aircraft Airbus 320 ATRA Henri Siller, Wolfram Hage, Timo Schumacher DLR Institute of Propulsion Technology,
More information