EFFECT OF REYNOLDS NUMBER ON THE UNSTEADY FLOW AND ACOUSTIC FIELDS OF SUPERSONIC CAVITY
|
|
- Leon Melton
- 5 years ago
- Views:
Transcription
1 Proceedings of FEDSM 03 4TH ASME_JSME Joint Fluids Engineering Conference Honolulu, Hawaii, USA, July 6 11, 2003 FEDSM EFFECT OF REYNOLDS NUMBER ON THE UNSTEADY FLOW AND ACOUSTIC FIELDS OF SUPERSONIC CAVITY A. Hamed, D. Basu and K. Das Department of Aerospace Engineering and Engineering Mechanics University of Cincinnati, Cincinnati, OH ABSTRACT Numerical simulations are conducted to study the flow and acoustic fields for unsteady supersonic turbulent flow over an open cavity using Detached Eddy Simulations for two different Reynolds numbers. Results are presented for pressure fluctuations history, vorticity iso-surfaces and turbulent kinetic energy and sound pressure levels spectra. The results reveal higher sound pressure levels (SPL), and finer scale structures within the cavity at the higher Reynolds number INTRODUCTION High speed flows over open cavities produce complex unsteady interactions, which are characterized by a severe acoustic environment. Such flow fields are comprised of both broadband small-scale fluctuations typical of turbulent shear layers, and discrete resonance whose frequency and amplitude depend upon the cavity geometry and external flow conditions. Recent research on cavity flow control [1,2,3,4,5] underlines the need for understanding the unsteady flow mechanisms involved in acoustic emissions and their control-. Simulation of cavity flow field is challenging because of the massive separation regions and the complex coupling between turbulence and acoustics through a feedback process that leads to large amplitude; self sustained flow oscillations [1]. Early correlations of cavity acoustic resonance frequency were developed by Rossiter [6] based on the linear acoustic theory. However, the amplitude of pressure oscillations and the SPL is more challenging to predict. Numerical investigations of flow over open cavities based on time dependent Reynolds Averaged Navier- Stokes (URANS) simulations have been carried out for both two-dimensional [7-10] and three-dimensional [11,12] configurations. In general, these RANS simulations did not capture the cavity acoustic field. This was attributed to excessive turbulent dissipation in the used turbulence models. In addition, some studies reported that some two-equation turbulence models damped the cavity flow-field unsteadiness [13,14]. Direct Numerical Simulations (DNS), which do not recourse to conventional turbulence models have been limited by computational resources requirements to laminar flow over 2- D cavity. Large Eddy Simulations (LES) reduce the grid resolution requirements by resolving the larger, energy containing scales and modeling the smaller, more homogeneous scales. Sinha et al. [13,17] developed a hybrid LES/RANS code and to perform 2-D cavity flow simulations and compared the VLES results with the URANS results. Rizzetta et al.[18] performed LES to study L/D = 5 cavity flow control on a parallel computing platform of IBM SP3 with 254 processors. The simulations which were conducted at Re = /ft required perturbation of the incoming flow variables to produce transition, and sufficiently long runs to generate statistically meaningful data for the LES simulations at the upstream boundary. Detached Eddy Simulations (DES) were initiated by Spalart et al. [19], who proposed that a single turbulence model can be used to function as a sub-grid scale model in the LES regions and as turbulence model in the RANS regions [20]. Hence, DES combined the fine-tuned RANS technology in the attached boundary layers and the power of LES in the separated region to enable three-dimensional unsteady Navier-Stokes simulations at high Reynolds number with realistic computational resources. Strelets [21] and Bush et al. [22] developed a Mentor s SST [23] based DES model through the introduction of an equivalent length scale, and implemented it into the WIND code [24]. Hamed et al. [14] used the SST based DES to investigate 3-D unsteady flow and acoustic fields in supersonic cavity. Our previous DNS investigations [16] demonstrated a dramatic increase in the pressure oscillations amplitude and the associated sound pressure level with free stream Mach number. However these DNS simulations were limited to laminar 2-D cavity. Subsequent DES investigations [14] revealed both broadband as well as tonal frequencies in the computed SPL spectra. In the present paper, the unsteady supersonic 3D cavity flow is investigated using SST [23] based DES model to 1 Copyright 2003 by ASME
2 determine the effects of Reynolds number on the flow and acoustic fields. METHODOLOGY Unsteady compressible viscous flow solutions for the Navier-Stokes equations in conservation law form were obtained using the WIND codes [24]. The SST based DES model was used in the present investigation. Based on prior RANS experience of the lead author [25] who assessed both S- A [20] and Menter s SST [23] models in the simulations of supersonic flow with larger separated flow regions in overexpanded supersonic nozzles. The solution domain for the inch cavity, allowed the turbulent boundary layer to develop on the flat plate upstream of the cavity s forward bulkhead. In order to maintain the incoming boundary layer thickness at 10% of the cavity depth D, the upstream plate length was 3D for the Reynolds number of /ft and 4.5D for the higher Reynolds number of /ft. Supersonic free stream conditions were specified at the upstream boundary and first order extrapolation was applied at the upper boundary, 3D above the cavity opening and at the downstream boundary, 3D behind the rear bulkhead. Periodic boundary conditions were specified at the lateral boundaries in the span-wise direction. The aspect ratio in the computational grid varied between 1 and 5 in all three directions. The grid was packed near the walls to maintain y + < 3 for the first grid point. The parallel computations were performed on a cluster of Linux machines using grid points in the stream-wise, normal and span-wise directions for Re = /ft and grid points for Re = /ft. Additional details about the computational grid are given in table 1. The third order upwind-biased Roe scheme was used for spatial discretization with TVD operator to suppress the numerical instabilities in the shear layer and near the shock waves. Explicit time marching scheme with Newton like subiterations was used for temporal advancement. The DES simulations were initiated in the unsteady mode and continued over 200,000 constant time-steps. It took 100,000 time steps to purge out the transient flow and establish resonance and the remaining 100,000 time steps to compute 20 cycles. RESULTS AND DISCUSSIONS The DES simulations were performed for the L/D = 5 and W/D = 0.5 cavity at free stream Mach number of 1.19 and Reynolds numbers of /ft and /ft. Computational results are presented for the pressure fluctuations, sound pressure levels and turbulent kinetic energy spectra, Mach number contours and vorticity iso-surfaces. Figure 1 presents sample pressure fluctuations histories near the front and rear bulkheads at the cavity mid-span. One can see that, in general, the pressure fluctuations are chaotic and the amplitude is higher at the rear bulkhead. The SPL spectra were computed from the pressure fluctuations based on 2048 sample data points. Figure 2 compares the computed sound pressure level (SPL) spectra variation along the cavity opening mid-span for the two Reynolds numbers. One can see that the SPL spectra have a broadband content with a wide range of frequency scales and that the SPL level increases towards the rear bulkhead. According to figure 2, the maximum SPL increased from 145 db to 160 db with the increase in Reynolds number from /ft. to /ft. Figure 3 shows sample turbulent kinetic energy (TKE) spectra in the shear layer near the cavity s rear bulkhead. One can see that the spectra have a broadband content over a wide range of frequency. The classical 5/3 Kolmogorov slope is shown in the figure for reference. Sample results for the axial vorticity iso-surfaces at Re= /ft are presented in figure 4. This figure demonstrates eddies formation within the cavity since the axial vorticity is zero in the incoming flow upstream of the cavity. The span-wise vorticity iso-surfaces are compared for the two Reynolds numbers in figure 5. They show the roll up of the shed vortex and the impingement of the shear layer on the rear bulkhead. Figure 5 shows a tangible deeper range of fine scale structures within the cavity at the high Reynolds number and a reduction in the size of the shed vortex. Figure 6 presents Mach number carpet plots at mid-span for the two Reynolds numbers. The figures show that an oblique shock is formed upstream of the cavity with a subsequent increase in the incoming boundary layer thickness due to shock interactions. One can see that the thickening of the boundary layer and the subsequent deflection of the shear layer is greater at the low Reynolds number. In addition to the different eddy structures inside the cavity, figure 5 shows that the Reynolds number also affects the shock and expansion waves pattern and strength outside the cavity. CONCLUSIONS Detached Eddy Simulations (DES) were performed to study the unsteady three-dimensional flow and acoustic fields of an open L/D = 5 cavity at free-stream Mach number of 1.19 for two different Reynolds numbers. The presented results reveal the basic flow features, including the vortex shedding, shock waves, the small scale eddy formation within the cavity and the three-dimensional flow characteristics. The results showed an increase in the range of predicted fine scale structures and an increase in the predicted SPL with the increase in Reynolds number ACKNOWLEDGMENTS This research was supported by a DAGSI grant AFRL/VA- UC-00-01; Mr. M. Stanek and Dr. M Visbal, technical monitors. The authors would like to thank Mr. Robert Ogden of UC for providing technical support with the linux cluster. 2 Copyright 2003 by ASME
3 REFERENCES 1) Kegerise, M. A., Spina, E. F., and Cattafesta, L. N. III, 1999, "An Experimental Investigation of Flow- Induced Cavity Oscillations," AIAA ) Stanek, M. J., Raman, G., Kibens, V., Ross, J. A., Odedra, J., Peto, J.W., 2000, Control of Cavity Resonance Through Very High Frequency Forcing, AIAA ) Stanek, M. J., Raman, G., Kibens, V., Ross, J. A., Odedra, J., Peto, J.W., 2001, Suppression of Cavity Resonance Using High Frequency Forcing The Characteristic Signature of Effective Devices, AIAA ) Shaw, Leonard., 2001, High speed application of active flow control for cavity acoustics, AIAA Paper ) Shaw, Leonard., Smith, Brian., Welterien, Tracy.,2001, Actuator optimization for active flow control of cavity acoustics, AIAA Paper ) Rossitter, J.E., 1964, Wind-Tunnel Experiments on the Flow over Rectangular Cavities at Subsonic and Transonic Speeds Royal Aircraft Establishment Reports and Memoranda No ) Grace, S., 2001, An overview of Computational Aeroacoustic Techniques applied to cavity noise prediction, AIAA Aerospace Sciences Meeting, Reno NV, AIAA ) Shih S. H, Hamed, A, Yeuan J. J., 1994, Unsteady Supersonic Cavity Flow Simulations Using Coupled Kappa-Epsilon and Navier-Stokes Equations, AIAA Journal, Vol. 32, No. 10, pp ) Tam, C-J., Orkwis, P. D., and Disimile, P. J., 1996, Algebraic Turbulence Model Simulations of Supersonic Open Cavity Flow Physics, AIAA Journal, Vol. 34, No. 11, pp ) Shang, J. S., and Hankey, W. L., 1980, Analyses of pressure oscillations in an open cavity, AIAA Journal, Vol. 18, No. 8, pp ) Rizzetta, D. P., 1988, Numerical Simulations of Supersonic flow over a three-dimensional cavity, AIAA Journal, Vol. 26, No. 7, pp ) Suhs, N., E., 1987, Computations of Three- Dimensional Cavity flow at Subsonic and Supersonic Mach numbers, AIAA ) Sinha, N., Dash, S. M., Chidambaram, N. and Findlay, D., 1998, A Perspective on the Simulation of Cavity Aeroacosutics, AIAA ) Hamed, A., Basu, D., and Das, K., 2003, "Detached Eddy Simulations of Supersonic Flow over Cavity," AIAA Paper , 41st AIAA Aerospace Sciences Meeting and Exhibit, Reno, Nevada. 15) Colonius, T., Basu, A. J., and Rowley, C. W., 1999, Numerical Investigation of the Flow Past a Cavity, AIAA ) Hamed, A., Basu, D., Mohamed, A. and Das, K., 2001, Direct Numerical Simulations of Unsteady Flow over Cavity, Proceedings 3rd AFOSR International Conference on DNS/LES (TAICDL), Arlington, Texas 17) Arunajatesan, S., Shipman, J. D., and Sinha, N., 2002, Hybrid RANS-LES simulation of cavity flow fields with control, AIAA ) Rizzetta, D. P. and Visbal, M. R., 2002, Large- Eddy Simulation of Supersonic Cavity Flowfields Including Flow Control, 32 nd AIAA Fluid Dynamics Conference, AIAA ) Spalart, P. R., Jou, W. H., Strelets, M., and Allmaras, S. R., 1997, Comments on the Feasibility of LES for Wings, and on a Hybrid RANS/LES Approach,, First AFOSR International Conference on DNS/LES, Ruston, Louisiana, USA. 20) Spalart, P. R., and Allmaras, S. R., 1994, A oneequation turbulence model for aerodynamic flows, La Rech. A reospatiale, Vol. 1, pp ) Strelets, M., 2001, Detached Eddy Simulation of Massively Separated Flows, 39 th AIAA Aerospace Sciences Meeting and Exhibit, AIAA ) Bush, R. H., and Mani, Mori, 2001 A twoequation large eddy stress model for high sub-grid shear, 31 st AIAA Computational Fluid Dynamics Conference, AIAA ) Menter, F. R., 1994, 2-Equation Eddy-Viscosity Turbulence Models For Engineering Applications, AIAA Journal, Vol. 32, No. 5, pp ) 25) Hamed, A., and Vogiatzis, C., 1997, Three- Dimensional Flow Computations and Thrust Predictions in 2DCD Overexpanded Nozzles, AIAA Copyright 2003 by ASME
4 Table 1: Summary of computational parameters for numerical simulations Reynolds Number Grid y minimum Grid Points Grids within BL ( ) Grid points within cavity /ft D 770, , /ft D 2,266, ,800 Near Front Bulkhead Near Rear Bulkhead Figure 1 Pressure fluctuation history (Re = /ft) Re= /ft Re= /ft Figure 2 Sound Pressure Level spectra 4 Copyright 2003 by ASME
5 Figure 3 Turbulent kinetic energy spectra in the cavity shear layer (Re= /ft) Figure 4 Iso-surfaces of axial vorticity component (Re= /ft) 5 Copyright 2003 by ASME
6 Re= /ft Re= /ft Figure 5 Iso-surfaces of span-wise vorticity Re= /ft Re= /ft Figure 6 Mach number contours at cavity mid-span 6 Copyright 2003 by ASME
DIRECT NUMERICAL SIMULATIONS OF HIGH SPEED FLOW OVER CAVITY. Abstract
3 rd AFOSR International Conference on DNS/LES (TAICDL), August 5-9 th, 2001, Arlington, Texas. DIRECT NUMERICAL SIMULATIONS OF HIGH SPEED FLOW OVER CAVITY A. HAMED, D. BASU, A. MOHAMED AND K. DAS Department
More informationFEDSM COMPUTATIONAL AEROACOUSTIC ANALYSIS OF OVEREXPANDED SUPERSONIC JET IMPINGEMENT ON A FLAT PLATE WITH/WITHOUT HOLE
Proceedings of FEDSM2007: 5 th Joint ASME/JSME Fluids Engineering Conference July 30-August 2, 2007, San Diego, CA, USA FEDSM2007-37563 COMPUTATIONAL AEROACOUSTIC ANALYSIS OF OVEREXPANDED SUPERSONIC JET
More informationStudies on the Transition of the Flow Oscillations over an Axisymmetric Open Cavity Model
Advances in Aerospace Science and Applications. ISSN 2277-3223 Volume 3, Number 2 (2013), pp. 83-90 Research India Publications http://www.ripublication.com/aasa.htm Studies on the Transition of the Flow
More informationSIMULATION OF THREE-DIMENSIONAL INCOMPRESSIBLE CAVITY FLOWS
ICAS 2000 CONGRESS SIMULATION OF THREE-DIMENSIONAL INCOMPRESSIBLE CAVITY FLOWS H Yao, R K Cooper, and S Raghunathan School of Aeronautical Engineering The Queen s University of Belfast, Belfast BT7 1NN,
More informationLES Study of Feedback-loop Mechanism of Supersonic Open Cavity Flows
40th Fluid Dynamics Conference and Exhibit 28 June - 1 July 2010, Chicago, Illinois AIAA 2010-5112 LES Study of Feedback-loop Mechanism of Supersonic Open Cavity Flows Weipeng Li 1 Dept. of Aeronautics
More informationCONTROL OF TRANSONIC CAVITY FLOW INSTABILITY BY STREAMWISE AIR INJECTION
CONTROL OF TRANSONIC CAVITY FLOW INSTABILITY BY STREAMWISE AIR INJECTION Aldo Rona Department of Engineering, University of Leicester, Leicester, LE1 7RH, UK ABSTRACT A time-dependent numerical model of
More informationNumerical Studies of Supersonic Jet Impingement on a Flat Plate
Numerical Studies of Supersonic Jet Impingement on a Flat Plate Overset Grid Symposium Dayton, OH Michael R. Brown Principal Engineer, Kratos/Digital Fusion Solutions Inc., Huntsville, AL. October 18,
More informationShock/boundary layer interactions
Shock/boundary layer interactions Turbulent compressible channel flows F.S. Godeferd Laboratoire de Mécanique des Fluides et d Acoustique Ecole Centrale de Lyon, France Journée Calcul Intensif en Rhône
More informationAvailable online at ScienceDirect. Procedia Engineering 79 (2014 ) 49 54
Available online at www.sciencedirect.com ScienceDirect Procedia Engineering 79 (2014 ) 49 54 37th National Conference on Theoretical and Applied Mechanics (37th NCTAM 2013) & The 1st International Conference
More informationLarge Eddy Simulation of Three-Stream Jets
Large Eddy Simulation of Three-Stream Jets J. Xiong 1, F. Liu 2, and D. Papamoschou 3 University of California, Irvine, Irvine, CA, 92697 We present a computational study of three-stream jets simulating
More informationAerodynamic noise produced in flow around an automobile bonnet
Aerodynamic noise produced in flow around an automobile bonnet Hiroshi Yokoyama 1, Takahiro Nakajima 2, Taishi Shinohara 3, Masashi Miyazawa 4 and Akiyoshi Iida 5 1,2,3,5 Department of Mechanical Engineering,
More informationWALL ROUGHNESS EFFECTS ON SHOCK BOUNDARY LAYER INTERACTION FLOWS
ISSN (Online) : 2319-8753 ISSN (Print) : 2347-6710 International Journal of Innovative Research in Science, Engineering and Technology An ISO 3297: 2007 Certified Organization, Volume 2, Special Issue
More informationNumerical Methods in Aerodynamics. Turbulence Modeling. Lecture 5: Turbulence modeling
Turbulence Modeling Niels N. Sørensen Professor MSO, Ph.D. Department of Civil Engineering, Alborg University & Wind Energy Department, Risø National Laboratory Technical University of Denmark 1 Outline
More informationThere are no simple turbulent flows
Turbulence 1 There are no simple turbulent flows Turbulent boundary layer: Instantaneous velocity field (snapshot) Ref: Prof. M. Gad-el-Hak, University of Notre Dame Prediction of turbulent flows standard
More informationNumerical Investigation of the Transonic Base Flow of A Generic Rocket Configuration
1 Numerical Investigation of the Transonic Base Flow of A Generic Rocket Configuration A. Henze, C. Glatzer, M. Meinke, W. Schröder Institute of Aerodynamics, RWTH Aachen University, Germany March 21,
More informationSimulations for Enhancing Aerodynamic Designs
Simulations for Enhancing Aerodynamic Designs 2. Governing Equations and Turbulence Models by Dr. KANNAN B T, M.E (Aero), M.B.A (Airline & Airport), PhD (Aerospace Engg), Grad.Ae.S.I, M.I.E, M.I.A.Eng,
More informationZonal hybrid RANS-LES modeling using a Low-Reynolds-Number k ω approach
Zonal hybrid RANS-LES modeling using a Low-Reynolds-Number k ω approach S. Arvidson 1,2, L. Davidson 1, S.-H. Peng 1,3 1 Chalmers University of Technology 2 SAAB AB, Aeronautics 3 FOI, Swedish Defence
More informationComputational Investigations of High-Speed Dual-Stream Jets
9th AIAA/CEAS Aeroacoustics Conference and Exhibit -4 May 3, Hilton Head, South Carolina AIAA 3-33 Computational Investigations of High-Speed Dual-Stream Jets Nicholas J. Georgiadis * National Aeronautics
More informationNumerical Study of Jet Plume Instability from an Overexpanded Nozzle
45th AIAA Aerospace Sciences Meeting and Exhibit 8 - January 27, Reno, Nevada AIAA 27-39 Numerical Study of Jet Plume Instability from an Overexpanded Nozzle Q. Xiao * and H.M. Tsai Temasek Laboratories,
More informationTurbulent eddies in the RANS/LES transition region
Turbulent eddies in the RANS/LES transition region Ugo Piomelli Senthil Radhakrishnan Giuseppe De Prisco University of Maryland College Park, MD, USA Research sponsored by the ONR and AFOSR Outline Motivation
More informationDETACHED-EDDY SIMULATION OF FLOW PAST A BACKWARD-FACING STEP WITH A HARMONIC ACTUATION
DETACHED-EDDY SIMULATION OF FLOW PAST A BACKWARD-FACING STEP WITH A HARMONIC ACTUATION Liang Wang*, Ruyun Hu*, Liying Li*, Song Fu* *School of Aerospace Engineering, Tsinghua University, Beijing 100084,
More informationNumerical investigation of the flow instabilities in centrifugal fan
Proceedings of the 4th WSEAS International Conference on Fluid Mechanics and Aerodynamics, Elounda, Greece, August 21-23, 26 (pp282-288) Numerical investigation of the flow instabilities in centrifugal
More informationAeroacoustics, Launcher Acoustics, Large-Eddy Simulation.
Seventh International Conference on Computational Fluid Dynamics (ICCFD7), Big Island, Hawaii, July 9-13, 2012 ICCFD7-2012-3104 ICCFD7-3104 Analysis of Acoustic Wave from Supersonic Jets Impinging to an
More informationNumerical Study of Pressure Waves Generated by H-IIA Launch Vehicle at Lift-off
Numerical Study of Pressure Waves Generated by H-IIA Launch Vehicle at Lift-off Seiji Tsutsumi, Taro Shimizu, Ryoji Takaki, Eiji Shima, and Kozo Fujii Japan Aerospace Exploration Agency 3-1-1 Yoshinodai,
More informationAEROACOUSTIC INVESTIGATION OF THE EFFECT OF A DETACHED FLAT PLATE ON THE NOISE FROM A SQUARE CYLINDER
Abstract AEROACOUSTIC INVESTIGATION OF THE EFFECT OF A DETACHED FLAT PLATE ON THE NOISE FROM A SQUARE CYLINDER Aniket D. Jagtap 1, Ric Porteous 1, Akhilesh Mimani 1 and Con Doolan 2 1 School of Mechanical
More informationIn the continuing effort to better understand hypersonic flow phenomena, mixing characteristics of various
50th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition 09-12 January 2012, Nashville, Tennessee AIAA 2012-0480 Hybrid LES / RANS Simulations of Shock-Distorted Injection
More informationNumerical Modelling of Aerodynamic Noise in Compressible Flows
Open Journal of Fluid Dynamics 22 2 65-69 http://dx.doi.org/.4236/ofd.22.237 Published Online September 22 (http://www.scirp.org/ournal/ofd) Numerical Modelling of Aerodynamic Noise in Compressible Flows
More informationUnderstanding of the Flow Behaviour on a Helmholtz Resonator Excited by Grazing Flow
Understanding of the Flow Behaviour on a Helmholtz Resonator Excited by Grazing Flow Abstract Grazing flow passing over the quiescent fluid inside the cavity of a Helmholtz resonator can excite the resonator.
More informationComputations of Turbulent Flow over an Aircraft Windshield Wiper Model
19th AIAA Computational Fluid Dynamics 22-25 June 2009, San Antonio, Texas AIAA 2009-3977 Computations of Turbulent Flow over an Aircraft Windshield Wiper Model Michael P. Urban 1 and Klaus A. Hoffmann
More informationAPPLICATION OF HYBRID CFD/CAA TECHNIQUE FOR MODELING PRESSURE FLUCTUATIONS IN TRANSONIC FLOWS
TASK QUARTERLY Vol. 17, Nos 3 4, 2013, pp. 145 154 APPLICATION OF HYBRID CFD/CAA TECHNIQUE FOR MODELING PRESSURE FLUCTUATIONS IN TRANSONIC FLOWS SŁAWOMIR DYKAS, WŁODZIMIERZ WRÓBLEWSKI AND SEBASTIAN RULIK
More informationThe Computations of Jet Interaction on a Generic Supersonic Missile
The Computations of Jet Interaction on a Generic Supersonic Missile *Jinbum Huh 1) and Seungsoo Lee 2) 1), 2) Department of Aerospace Engineering, Inha Univ., Incheon, Korea 2) slee@inha.ac.kr ABSTRACT
More informationSG Turbulence models for CFD
SG2218 2012 Turbulence models for CFD Stefan Wallin Linné FLOW Centre Dept of Mechanics, KTH Dept. of Aeronautics and Systems Integration, FOI There are no simple turbulent flows Turbulent boundary layer:
More informationASSESSMENT OF RANS AND DES METHODS FOR THE AHMED BODY
ECCOMAS Congress 2016 VII European Congress on Computational Methods in Applied Sciences and Engineering M. Papadrakakis, V. Papadopoulos, G. Stefanou, V. Plevris (eds.) Crete Island, Greece, 5 10 June
More informationGlobal Structure of Buffeting Flow on Transonic Airfoils
Global Structure of Buffeting Flow on Transonic Airfoils J.D. Crouch, A. Garbaruk, D. Magidov, and L. Jacquin Abstract The flow field associated with transonic airfoil buffet is investigated using a combination
More informationNumerical Simulation of a Blunt Airfoil Wake
6th Australasian Fluid Mechanics Conference Crown Plaza, Gold Coast, Australia 2-7 December 7 Numerical Simulation of a Blunt Airfoil Wake C.J. Doolan School of Mechanical Engineering University of Adelaide,
More informationcompression corner flows with high deflection angle, for example, the method cannot predict the location
4nd AIAA Aerospace Sciences Meeting and Exhibit 5-8 January 4, Reno, Nevada Modeling the effect of shock unsteadiness in shock-wave/ turbulent boundary layer interactions AIAA 4-9 Krishnendu Sinha*, Krishnan
More informationComputational Fluid Dynamics Analysis of Jets with Internal Forced Mixers
Computational Fluid Dynamics Analysis of Jets with Internal Forced Mixers L. A. Garrison A. S. Lyrintzis G. A. Blaisdell Purdue University, West Lafayette, IN, 47907, USA W. N. Dalton Rolls-Royce Corporation,
More informationEXPERIMENTAL STUDY ON HYPERSONIC HEATING CHARACTERISTICS OF CAVITY WAKE FLOW
24 TH INTERNATIONAL CONGRESS OF THE AERONAUTICAL SCIENCES EXPERIMENTAL STUDY ON HYPERSONIC HEATING CHARACTERISTICS OF CAVITY WAKE FLOW Koichi HOZUMI*, Tadao KOYAMA**, Noriaki HIRABAYASHI** *Foundation
More informationCFD Analysis of Micro-Ramps for Hypersonic Flows Mogrekar Ashish 1, a, Sivakumar, R. 2, b
Applied Mechanics and Materials Submitted: 2014-04-25 ISSN: 1662-7482, Vols. 592-594, pp 1962-1966 Revised: 2014-05-07 doi:10.4028/www.scientific.net/amm.592-594.1962 Accepted: 2014-05-16 2014 Trans Tech
More informationOver-expansion Effects on Mach 3.0 Supersonic Jet Acoustics
14th AIAA/CEAS Aeroacoustics Conference (29th AIAA Aeroacoustics Conference) 5-7 May 28, Vancouver, British Columbia Canada AIAA 28-286 Over-expansion Effects on Mach. Supersonic Jet Acoustics Taku Nonomura
More informationCLOSED-LOOP CONTROL OF FLOW-INDUCED CAVITY OSCILLATIONS
CLOSED-LOOP CONTROL OF FLOW-INDUCED CAVITY OSCILLATIONS By QI SONG A DISSERTATION PRESENTED TO THE GRADUATE SCHOOL OF THE UNIVERSITY OF FLORIDA IN PARTIAL FULFILLMENT OF THE REQUIREMENTS FOR THE DEGREE
More informationNUMERICAL INVESTIGATIONS ON FLOW CHARACTERISTICS OVER A CAVITY RELATING PRESSURE FIELD AND COEFFICIENT OF PRESSURE THROUGH LES-APPROACH
NUMERICAL INVESTIGATIONS ON FLOW CHARACTERISTICS OVER A CAVITY RELATING PRESSURE FIELD AND COEFFICIENT OF PRESSURE THROUGH LES-APPROACH Dr. Nirmal Kumar Kund Associate Professor, Department of Production
More informationPrediction of noise from a wing-in-junction flow using computational fluid dynamics
Proceedings of Acoustics - Fremantle -3 November, Fremantle, Australia Prediction of noise from a wing-in-junction flow using computational fluid dynamics Con J. Doolan, Jesse L. Coombs, Danielle J. Moreau,
More informationParallel Computations of Unsteady Three-Dimensional Flows in a High Pressure Turbine
Parallel Computations of Unsteady Three-Dimensional Flows in a High Pressure Turbine Dongil Chang and Stavros Tavoularis Department of Mechanical Engineering, University of Ottawa, Ottawa, ON Canada Stavros.Tavoularis@uottawa.ca
More informationNumerical Investigation of Shock wave Turbulent Boundary Layer Interaction over a 2D Compression Ramp
Advances in Aerospace Science and Applications. ISSN 2277-3223 Volume 4, Number 1 (2014), pp. 25-32 Research India Publications http://www.ripublication.com/aasa.htm Numerical Investigation of Shock wave
More informationThe Very Near Pressure Field of Three-Stream Jets
The Very Near Pressure Field of Three-Stream Jets A. Adam, D. Papamoschou, J. Xiong, and F. Liu University of California, Irvine, Irvine, CA, 92697, USA Using large eddy simulation (LES) of a hot coaxial
More informationBoundary-Layer Theory
Hermann Schlichting Klaus Gersten Boundary-Layer Theory With contributions from Egon Krause and Herbert Oertel Jr. Translated by Katherine Mayes 8th Revised and Enlarged Edition With 287 Figures and 22
More informationINVESTIGATION OF FLOW PARAMETERS AND NOISE OF SUBSONIC AND SUPERSONIC JETS USING RANS/ILES HIGH RESOLUTION METHOD
INVESTIGATION OF FLOW PARAMETERS AND NOISE OF SUBSONIC AND SUPERSONIC JETS USING RANS/ILES HIGH RESOLUTION METHOD L.A. Benderskiy, D.A. Lyubimov Central Institute of Aviation Motors, Russia Leosun.Ben@gmail.com
More informationSimulation of Aeroelastic System with Aerodynamic Nonlinearity
Simulation of Aeroelastic System with Aerodynamic Nonlinearity Muhamad Khairil Hafizi Mohd Zorkipli School of Aerospace Engineering, Universiti Sains Malaysia, Penang, MALAYSIA Norizham Abdul Razak School
More informationSTUDY OF THREE-DIMENSIONAL SYNTHETIC JET FLOWFIELDS USING DIRECT NUMERICAL SIMULATION.
42 nd AIAA Aerospace Sciences Meeting and Exhibit 5-8 January 2004/Reno, NV STUDY OF THREE-DIMENSIONAL SYNTHETIC JET FLOWFIELDS USING DIRECT NUMERICAL SIMULATION. B.R.Ravi * and R. Mittal, Department of
More informationIntroduction to Turbulence AEEM Why study turbulent flows?
Introduction to Turbulence AEEM 7063-003 Dr. Peter J. Disimile UC-FEST Department of Aerospace Engineering Peter.disimile@uc.edu Intro to Turbulence: C1A Why 1 Most flows encountered in engineering and
More informationRay traces through unsteady jet turbulence
aeroacoustics volume 1 number 1 2002 pages 83 96 83 Ray traces through unsteady jet turbulence J. B. Freund 1 and T. G. Fleischman 2 1 Theoretical and Applied Mechanics, University of Illinois at Urbana-Champaign
More informationResolving the dependence on free-stream values for the k-omega turbulence model
Resolving the dependence on free-stream values for the k-omega turbulence model J.C. Kok Resolving the dependence on free-stream values for the k-omega turbulence model J.C. Kok This report is based on
More informationNoise Generation Analysis of a Cylindrical Cavity by LES and Global Instability
Noise Generation Analysis of a Cylindrical Cavity by LES and Global Instability Fabien Mery ONERA, Toulouse, France Daniel C. Mincu ONERA, Chatillon, France Alois Sengissen Airbus, Toulouse, France Gregoire
More informationURANS Computations of Cavitating Flow around a 2-D Wedge by Compressible Two-Phase Flow Solver
URANS Computations of Cavitating Flow around a 2-D Wedge by Compressible Two-Phase Flow Solver *Yohan Choe 1), Hyeongjun Kim 1), Chongam Kim 2) 1), 2) Department of Aerospace Engineering, Seoul National
More informationJournal of Fluid Science and Technology
Science and Technology LDV and PIV Measurements of the Organized Oscillations of Turbulent Flow over a Rectangular Cavity* Takayuki MORI ** and Kenji NAGANUMA ** **Naval Systems Research Center, TRDI/Ministry
More informationSTAR-CCM+: NACA0012 Flow and Aero-Acoustics Analysis James Ruiz Application Engineer January 26, 2011
www.cd-adapco.com STAR-CCM+: NACA0012 Flow and Aero-Acoustics Analysis James Ruiz Application Engineer January 26, 2011 Introduction The objective of this work is to prove the capability of STAR-CCM+ as
More informationChapter 5 Phenomena of laminar-turbulent boundary layer transition (including free shear layers)
Chapter 5 Phenomena of laminar-turbulent boundary layer transition (including free shear layers) T-S Leu May. 3, 2018 Chapter 5: Phenomena of laminar-turbulent boundary layer transition (including free
More informationProceedings of the 4th Joint US-European Fluids Engineering Division Summer Meeting ASME-FEDSM2014 August 3-7, 2014, Chicago, Illinois, USA
Proceedings of the 4th Joint US-European Fluids Engineering Division Summer Meeting ASME-FEDSM4 August 3-7, 4, Chicago, Illinois, USA FEDSM4-38 SUPPRESSION OF UNSTEADY VORTEX SHEDDING FROM A CIRCULAR CYLINDER
More information1976. Numerical computation and optimization design of pantograph aerodynamic noise
1976. Numerical computation and optimization design of pantograph aerodynamic noise Ya-hui Wang North China University of Water Resources and Electric Power, Zhengzhou, China E-mail: wangyahui_1979@163.com
More informationAA214B: NUMERICAL METHODS FOR COMPRESSIBLE FLOWS
AA214B: NUMERICAL METHODS FOR COMPRESSIBLE FLOWS 1 / 29 AA214B: NUMERICAL METHODS FOR COMPRESSIBLE FLOWS Hierarchy of Mathematical Models 1 / 29 AA214B: NUMERICAL METHODS FOR COMPRESSIBLE FLOWS 2 / 29
More informationDetached Eddy Simulation on Hypersonic Base Flow Structure of Reentry-F Vehicle
Available online at www.sciencedirect.com ScienceDirect Procedia Engineering 00 (2014) 000 000 www.elsevier.com/locate/procedia APISAT2014, 2014 Asia-Pacific International Symposium on Aerospace Technology,
More informationINVESTIGATION OF THE FLOW OVER AN OSCILLATING CYLINDER WITH THE VERY LARGE EDDY SIMULATION MODEL
ECCOMAS Congress 2016 VII European Congress on Computational Methods in Applied Sciences and Engineering M. Papadrakakis, V. Papadopoulos, G. Stefanou, V. Plevris (eds.) Crete Island, Greece, 5 10 June
More informationHybrid RANS/LES Simulations of Supersonic base flow
Hybrid RANS/LES Simulations of Supersonic base flow Franck SIMON, Sébastien DECK *, Philippe GUILLEN, Pierre SAGAUT Applied Aerodynamics Department, Châtillon, France * Speaker Contents Context Test case
More informationToshinori Watanabe Department of Aeronautics and Astronautics The University of Tokyo Tokyo, Japan
Review: Active Control of Shock-associated Unsteady Flow Phenomena in Aeroengines - Suppression Techniques for Transonic Cascade Flutter and Supersonic Jet Noise - Toshinori Watanabe Department of Aeronautics
More informationNear-wall Reynolds stress modelling for RANS and hybrid RANS/LES methods
Platzhalter für Bild, Bild auf Titelfolie hinter das Logo einsetzen Near-wall Reynolds stress modelling for RANS and hybrid RANS/LES methods Axel Probst (now at: C 2 A 2 S 2 E, DLR Göttingen) René Cécora,
More informationInvestigation of the unsteady flow and noise sources generation in a slat cove: hybrid zonal RANS/LES simulation and dedicated experiment
20th AIAA Computational Fluid Dynamics Conference 27-30 June 2011, Honolulu, Hawaii AIAA 2011-3203 Investigation of the unsteady flow and noise sources generation in a slat cove: hybrid zonal RANS/LES
More informationDESIGN & COMPUTATIONAL FLUID DYNAMICS ANALYSES OF AN AXISYMMETRIC NOZZLE AT TRANSONIC FREE STREAM CONDITIONS
DESIGN & COMPUTATIONAL FLUID DYNAMICS ANALYSES OF AN AXISYMMETRIC NOZZLE AT TRANSONIC FREE STREAM CONDITIONS S Wasim Akram 1, S. Rajesh 2 1 M.Tech Student, Department of Mechanical Engineering, Krishna
More informationImplicit Large Eddy Simulation of Transitional Flow over a SD7003 Wing Using High-order Spectral Difference Method
40th Fluid Dynamics Conference and Exhibit 28 June - 1 July 2010, Chicago, Illinois AIAA 2010-4442 Implicit Large Eddy Simulation of Transitional Flow over a SD7003 Wing Using High-order Spectral Difference
More informationVortex Shedding and Wave Propagation in Transonic Two-dimensional Cavity Flows
2001 The Visualization Society of Japan and Ohmsha, Ltd. Journal of Visualization, Vol. 3, No. 4 (2001) 331-339 Vortex Shedding and Wave Propagation in Transonic Two-dimensional Cavity Flows Khan, M. U.*
More informationUWE has obtained warranties from all depositors as to their title in the material deposited and as to their right to deposit such material.
Khali, E. H. and Yao, Y. (2015) Mixing flow characteristics for a transverse sonic jet injecting into a supersonic crossflow. In: 53rd AIAA Aerospace Sciences Meeting: AIAA 2015 Sci-Tech Conference, Kissimmee,
More informationOn self-sustained oscillations in two-dimensional compressible flow over rectangular cavities
J. Fluid Mech. (22), vol. 455, pp. 315 346. c 22 Cambridge University Press DOI: 1.117/S2211217534 Printed in the United Kingdom 315 On self-sustained oscillations in two-dimensional compressible flow
More informationLARGE EDDY SIMULATION OF FLOW OVER NOZZLE GUIDE VANE OF A TRANSONIC HIGH PRESSURE TURBINE
20 th Annual CFD Symposium, August 09-10, 2018, Bangalore LARGE EDDY SIMULATION OF FLOW OVER NOZZLE GUIDE VANE OF A TRANSONIC HIGH PRESSURE TURBINE Bharathan R D, Manigandan P, Vishal Tandon, Sharad Kapil,
More informationChapter 1: Basic Concepts
What is a fluid? A fluid is a substance in the gaseous or liquid form Distinction between solid and fluid? Solid: can resist an applied shear by deforming. Stress is proportional to strain Fluid: deforms
More informationNumerical investigation of swirl flow inside a supersonic nozzle
Advances in Fluid Mechanics IX 131 Numerical investigation of swirl flow inside a supersonic nozzle E. Eslamian, H. Shirvani & A. Shirvani Faculty of Science and Technology, Anglia Ruskin University, UK
More informationLarge-eddy simulation of jet mixing in a supersonic turbulent crossflow
Center for Turbulence Research Annual Research Briefs 8 9 Large-eddy simulation of jet mixing in a supersonic turbulent crossflow By S. Kawai AN S. K. Lele. Motivation and objectives Important recent research
More informationarxiv: v1 [physics.flu-dyn] 1 Jun 2017
This draft was prepared using the LaTeX style file belonging to the Journal of Fluid Mechanics 1 arxiv:1706.00300v1 [physics.flu-dyn] 1 Jun 2017 Biglobal instabilities of compressible open-cavity flows
More informationExperimental investigation of flow control devices for the reduction of transonic buffeting on rocket afterbodies
Experimental investigation of flow control devices for the reduction of transonic buffeting on rocket afterbodies F.F.J. Schrijer 1, A. Sciacchitano 1, F. Scarano 1 1: Faculty of Aerospace Engineering,
More informationOn the aeroacoustic tonal noise generation mechanism of a sharp-edged. plate
On the aeroacoustic tonal noise generation mechanism of a sharp-edged plate Danielle J. Moreau, Laura A. Brooks and Con J. Doolan School of Mechanical Engineering, The University of Adelaide, South Australia,
More informationHigh speed PIV applied to aerodynamic noise investigation
Exp Fluids (11) 5:863 876 DOI 1.17/s348-1-935-8 RESEARCH ARTICLE High speed applied to aerodynamic noise investigation V. Koschatzky P. D. Moore J. Westerweel F. Scarano B. J. Boersma Received: 11 December
More informationJet Noise Analysis of a Mixed Turbofan Engine
Jet Noise Analysis of a Mixed Turbofan Engine Jens TRÜMNER 1 ; Christian MUNDT 2 1,2 Institute for Thermodynamics, UniBw München, Germany ABSTRACT Due to constantly increasing flight traffic the aircraft
More informationNUMERICAL SIMULATION AND MODELING OF UNSTEADY FLOW AROUND AN AIRFOIL. (AERODYNAMIC FORM)
Journal of Fundamental and Applied Sciences ISSN 1112-9867 Available online at http://www.jfas.info NUMERICAL SIMULATION AND MODELING OF UNSTEADY FLOW AROUND AN AIRFOIL. (AERODYNAMIC FORM) M. Y. Habib
More information886. Aeroacoustic noise reduction design of a landing gear structure based on wind tunnel experiment and simulation
886. Aeroacoustic noise reduction design of a landing gear structure based on wind tunnel experiment and simulation Xue Caijun 1, Zheng Guang 2, Tang Wei 3, Long Shuangli 4 Key Laboratory of Fundamental
More informationAERODYNAMIC SHAPING OF PAYLOAD FAIRING FOR A LAUNCH VEHICLE Irish Angelin S* 1, Senthilkumar S 2
e-issn 2277-2685, p-issn 2320-976 IJESR/May 2014/ Vol-4/Issue-5/295-299 Irish Angelin S et al./ International Journal of Engineering & Science Research AERODYNAMIC SHAPING OF PAYLOAD FAIRING FOR A LAUNCH
More informationCurriculum Vitae of Sergio Pirozzoli
Curriculum Vitae of Sergio Pirozzoli Address University of Rome La Sapienza Department of Mechanical and Aerospace Engineering Via Eudossiana 18 00184, Roma Contact tel.: +39 06 44585202 fax : +39 06 4881759
More information41st Aerospace Sciences Meeting and Exhibit 6-9 January 2003, Reno, Nevada Modeling shock unsteadiness in shock/turbulence interaction
4st Aerospace Sciences Meeting and Exhibit 6-9 January 003, Reno, Nevada Modeling shock unsteadiness in shock/turbulence interaction AIAA 003-65 Krishnendu Sinha*, Krishnan Mahesh and Graham V. Candler
More informationImplicit Solution of Viscous Aerodynamic Flows using the Discontinuous Galerkin Method
Implicit Solution of Viscous Aerodynamic Flows using the Discontinuous Galerkin Method Per-Olof Persson and Jaime Peraire Massachusetts Institute of Technology 7th World Congress on Computational Mechanics
More informationUNCLASSIFIED UNCLASSIFIED
UNCLASSIFIED Defense Technical Information Center Compilation Part Notice ADPO 13706 TITLE: Energy- Containing-Range Modeling of Fully-Developed Channel Flow Using a Hybrid RANS/LES Technique DISTRIBUTION:
More informationAttached and Detached Eddy Simulation
Attached and Detached Eddy Simulation Philippe R. Spalart Boeing Commercial Airplanes, Seattle, USA Mikhail K. Strelets Saint-Petersburg Polytechnic University and New Technologies and Services (NTS),
More informationRECONSTRUCTION OF TURBULENT FLUCTUATIONS FOR HYBRID RANS/LES SIMULATIONS USING A SYNTHETIC-EDDY METHOD
RECONSTRUCTION OF TURBULENT FLUCTUATIONS FOR HYBRID RANS/LES SIMULATIONS USING A SYNTHETIC-EDDY METHOD N. Jarrin 1, A. Revell 1, R. Prosser 1 and D. Laurence 1,2 1 School of MACE, the University of Manchester,
More informationDelayed Detached Eddy Simulation of Supersonic Inlet Buzz
Delayed Detached Eddy Simulation of Supersonic Inlet Buzz S. Trapier, S. Deck and P. Duveau Applied Aerodynamics Department What is Supersonic inlet buzz? Supersonic air inlets supply the engine of an
More informationSupersonic Windtunnel Noise Attenuation
Ryerson University Digital Commons @ Ryerson Theses and dissertations 1-1-2012 Supersonic Windtunnel Noise Attenuation William Wai Lim Wong Ryerson University Follow this and additional works at: http://digitalcommons.ryerson.ca/dissertations
More informationCHAPTER 7 SEVERAL FORMS OF THE EQUATIONS OF MOTION
CHAPTER 7 SEVERAL FORMS OF THE EQUATIONS OF MOTION 7.1 THE NAVIER-STOKES EQUATIONS Under the assumption of a Newtonian stress-rate-of-strain constitutive equation and a linear, thermally conductive medium,
More informationTheoretical Gas Flow through Gaps in Screw-type Machines
Theoretical Gas Flow through Gaps in Screw-type Machines Prof. Dr.-Ing. K. Kauder, Dipl.-Ing. D. Stratmann University of Dortmund, Fachgebiet Fluidenergiemaschinen (The experimental part of these studies
More informationAIAA Computational Analysis of a Pylon-Chevron Core Nozzle Interaction
Computational Analysis of a Pylon-Chevron Core Nozzle Interaction R.H.Thomas, K.W.Kinzie, and S. Paul Pao NASA Langley Research Center Hampton, VA USA 7 th AIAA/CEAS Aeroacoustics Conference 28-30 May
More informationNumerical study of the effects of trailing-edge bluntness on highly turbulent hydro-foil flows
Numerical study of the effects of trailing-edge bluntness on highly turbulent hydro-foil flows T. Do L. Chen J. Tu B. Anderson 7 November 2005 Abstract Flow-induced noise from fully submerged lifting bodies
More informationDYNAMIC SEPARATION CONTROL IN A LOW-SPEED ASYMMETRIC DIFFUSER WITH VARYING DOWNSTREAM BOUNDARY CONDITION
AIAA 23-4161 DYNAMIC SEPARATION CONTROL IN A LOW-SPEED ASYMMETRIC DIFFUSER WITH VARYING DOWNSTREAM BOUNDARY CONDITION Samantha H. Feakins, Douglas G. MacMartin, and Richard M. Murray California Institute
More informationDirect Numerical Simulation of Jet Actuators for Boundary Layer Control
Direct Numerical Simulation of Jet Actuators for Boundary Layer Control Björn Selent and Ulrich Rist Universität Stuttgart, Institut für Aero- & Gasdynamik, Pfaffenwaldring 21, 70569 Stuttgart, Germany,
More informationNumerical Computations of Internal Combustion Engine related Transonic and Unsteady Flows
Numerical Computations of Internal Combustion Engine related Transonic and Unsteady Flows by Olle Bodin February 2009 Technical Reports from Royal Institute of Technology KTH Mechanics SE-100 44 Stockholm,
More informationMultidisciplinary Applications of Detached-Eddy Simulation to Separated Flows at High Reynolds Numbers
Multidisciplinary Applications of Detached-Eddy Simulation to Separated Flows at High Reynolds Numbers Scott A. Morton, Matt Steenman, James R. Forsythe and Kenneth Kyle D. Squires and Russell M. Cummings
More information