Fundamental Study of Aero Acoustic Emission of Single and Tandem Cylinder Winson Lim Tan Chun Hern Voo Keng Soon Vince 05 Nov 12 Slide 1
Brief Review of Flow Over Cylinder Slide 2
Rationale Landing gear system major contributor to airframe noise during approach Cylinder like structure includes: Gear main strut, hydraulic lines, brake pistons, wheels and axles Unsteady wake interacts with downstream components to create dominant noise sources Tandem cylinder simplified prototype Models component level interactions To understand noise generation mechanism and achieve reduction of airframe noise Slide 3
Wake Characteristics of a Wake Behind a Cylinder At very low Re number < 49, the wake is steady and the wake comprises of two symmetrically placed vortices on each side of the wake At higher Re number, the wake becomes unsteady forming a vortex street as seen in (b) Slide 4
Wake Shedding Frequency vs Re from Single Cylinder Simulated Re in current study Slide 5
Flow Interference Flow Characteristics (Cylinders in Tandem) Flow interference imposes continuous and discontinuous changes in vortex shedding Cylinder oscillations modified by and strongly dependent on cylinder arrangement Slide 6
Wake Shedding States (Cylinders in Tandem) 0.20 Upstream & Downstream Cylinder CL vs Time (DES) 1.50 0.15 0.10 1.00 CL_Upstream 0.05 0.00-0.05-0.10 0.50 0.00-0.50 CL_Downstream Critical tandem cylinder spacing configuration of L/D = 3.7 chosen -0.15 0.02 0.07 0.12 0.17-0.20 Time t/s CL_Upstream CL_Downstream -1.00-1.50 Bistable flow state exists between cylinders Constant shedding state Intermittent shedding state Slide 7
CFD Simulations of Cylinder Flow at Re = 3900 (URANS, LES & DES) Slide 8
Meshing and Testing Conditions Trimmer mesh of 3 million cells URANS,LES,DES Diameter of 20mm and span of 80mm (4D) Periodic boundary conditions at cylinder ends Time Step: 1.0e-5 sec Reynolds Number studied: 3900 Aeroacoustics module: Ffowcs Williams Hawkings Microphone Positions Z Y X Slide 9
Cd 1.5 1.4 1.3 1.2 1.1 1.0 0.9 0.8 0.7 0.6 0.5 0.4 0.3 0.2 0.1 0.0-0.1-0.2-0.3-0.4-0.5-0.6-0.7-0.8-0.9-1.0-1.1-1.2 Comparison of Time Averaged Results (Re=3900) Cases Span Cd Strouhal no. Experimental 4D 1.01 0.205 URANS 4D 1.078 0.214 LES 4D 0.998 0.213 DES 4D 1.088 0.196 Cd and CL vs Time (DES simulation) 60 160 260 Time t (U/D) 1.5 1.4 1.3 1.2 1.1 1 0.9 0.8 0.7 0.6 0.5 0.4 0.3 0.2 0.1 0-0.1-0.2-0.3-0.4-0.5-0.6-0.7-0.8-0.9-1 -1.1-1.2-1.3-1.4-1.5 CL Far Field Frequency of 333 Hz -> Strouhal no. ~0.196 Slide 10
0.2250 0.2000 0.1750 Streamwise Reynolds Stresses <u'u'> vs z/d at x/d=1.54 plane DES DES predicts comparable peak values as compared to exp results Higher level of mixing predicted at the wake centre 0.1500 0.1250 0.1000 < u u LES LES under predicts peak values as compared to exp results 0.0750 0.0500 0.0250 0.0000 z/d -3.0-2.0-1.0 0.0 1.0 2.0 3.0 Experiment DES URANS LES Streamwise Reynolds Stress URANS URANS under predicts <u'u'> in the wake Slide 11
Shear & Spanwise Reynolds Stress 0.2000 0.1500 <u v'> vs z/d at x/d=1.54 plane 0.0990 0.0890 <w w'> vs z/d at x/d=1.54 plane 0.1000 0.0500 0.0000-0.0500-0.1000-0.1500-0.2000 <u v'> z/d -2.0-1.0 0.0 1.0 2.0 Experiment URANS LES DES 0.0790 0.0690 0.0590 0.0490 0.0390 0.0290 0.0190 <w w'> 0.0090-0.0010-3.0-2.0-1.0 0.0 1.0 2.0 3.0 Experiment z/d URANS LES DES Slide 12
Flow Structures Visualized by the Q Criteria (DES simulation, Re=3900) Pairs of counterrotating streamwise vortices -> Karman vortex shedding characteristics Longitudinal vortices interlaced between counter-rotating vortices Slide 13
OSPL Comparison at 70 Diameter Cases WT data (Journal of Sound and Vibration) Overall Sound Pressure Level (OSPL) Peak Frequency Peak Strouhal no. 83.8 308 0.193 DES 83.6 313 0.196 Receiver position 70D D Slide 14
Far-Field Sound Directivity Pattern ΔP'rms vs Receiver Positions 165 150 135 120 115 0.0001 0.00008 0.00006 0.00004 0.00002 90 75 60 45 30 15 Far field directivity pattern exemplify the characteristics of dipole sound propagation 180 0 0 195 210 225 315 330 345 Microphones are placed at 70D around the cylinder monitoring total pressure Compute the ΔP rms (pressure fluctuation component) at r=70d, non-dimensionalised by free stream velocity and density 240 255 270 285 300 Slide 15
CFD Simulations of Cylinder Flow at Re = 46,000 (DES) Slide 16
Meshing and Testing Conditions Trimmer mesh of 3.6 million cells DES Diameter of 9.8mm and span of 29.4mm (3D) Periodic boundary conditions at cylinder ends Time Step: 1.0e-5 sec Reynolds Number studied: 46000 Aeroacoustics module: Ffowcs Williams Hawkings Microphone Positions Z Y X Slide 17
Time Averaged Results for Re = 46000 Cases C D,average C D,rms Strouhal no. Experimental 1.35 0.16 0.19 LES_OpenLit 1.24 0.10 0.19 1.90 1.70 1.50 1.30 1.10 0.90 0.70 0.50 0.30 0.10-0.10-0.30-0.50-0.70-0.90-1.10-1.30-1.50 DES_current 1.235 0.141 0.20 C D C L C L Time t(u/d) 300 350 400 450 500 550 C D,average C L,average Far Field Frequency of 1455.8 Hz - > Strouhal no. ~0.20 Slide 18
0.200 Reynolds Stresses Characteristics at x/d=1.54 (Re=46,000) <u'u'> vs z/d 0.060 <w w'> vs z/d 0.150 0.100 0.050 0.000 0.600 0.500 0.400 0.300 0.200 0.100 0.000 <u'u'> <v v'> z/d -3-2 -1 0 1 2 3 <v v'> vs z/d z/d -3-2 -1 0 1 2 3 0.050 0.040 0.030 0.020 0.010 0.000 0.150 0.100 0.050 0.000-0.050-0.100-0.150 <w w'> z/d -3-2 -1 0 1 2 3 <u v'> <u v'> vs z/d z/d -3-2 -1 0 1 2 3 Trends of the Reynolds stresses are typical to that of a turbulent wake Slide 19
Flow Structures Visualized by the Q Criteria (DES simulation, Re=46,000) Slide 20
Sound Directivity Pattern in terms of Prms & OSPL ΔP'rms vs Receiver Positions 165 180 195 150 210 135 1.40E-04 120 115 1.20E-04 1.00E-04 8.00E-05 6.00E-05 4.00E-05 2.00E-05 0.00E+00 225 240 255 90 270 75 60 45 315 300 285 30 15 0 330 345 SPL vs Receiver Positions 90 100 120 60 80 150 60 30 40 20 180 210 0 0 330 240 300 270 SPL of Experiment 91dB SPL of DES~92dB Occurring at 1455.8Hz which corresponds to St number of 0.20 SPL at other positions match quite closely between experimental and CFD results DES Experiment Slide 21
CFD Simulations of Tandem Cylinder Flow at Re = 1.66E5 (DES) Slide 22
Meshing and Testing Conditions Trimmer mesh of 6.2 million cells DES (K-w sst) Diameter of 57.15mm and span of 171.45mm (3D) Periodic boundary conditions at cylinder ends Time Step: 2.0e-5 sec Physical Time Simulated: 0.216 sec Reynolds Number studied: 1.66E5 Aeroacoustics module: Ffowcs Williams Hawkings Z Y Microphone Positions X Slide 23
Comparison of Time Averaged Results Upstream 90 Deg Experiment CFD(Literature) DES_Near field DES_Far field Span 18D 18D 3D 3D Frequency 178Hz 166Hz 158Hz 166Hz Strouhal no. 0.232 0.219 0.203 0.213 Near field Frequency of 158 Hz -> Strouhal no. ~0.203 140 120 DES Far field Frequency of 166 Hz -> Strouhal no. ~0.213 100 PSD (db/hz) 80 60 40 20 0 10 100 Frequency 1000 DES_Far field DES_Near field Slide 24
Counter-rotating streamwise vortices observed in intercylinder flow region Constant shedding flow state upstream Flow Structures Visualized by the Q Criteria (DES simulation, Re=1.66E5) Wake interference amplifies downstream shedding and oscillation Only shear layer roll up is observed in inter-cylinder flow region Intermittent shedding state upstream Wake interference damp out downstream shedding and oscillation Slide 25
PSD (db/hz) 130 120 110 100 90 80 Near Field Pressure Spectra Upstream Cylinder 90 deg Spectra Downstream Cylinder 90 deg Spectra 140 130 120 PSD (db/hz) 110 100 90 80 70 10 100 1000 Frequency DES Literature_CFD Literature_Experimental 70 10 100 1000 Frequency DES Literature_CFD Literature_Experimental Shedding frequency of near field spectra in good agreement with literature CFD results. Deviation in peak values could be attributed to insufficient simulation time, where the bistable flow behaviour have yet to be statistically converged. Slide 26
A B Microphone Spectra at 30D ~30D C PSD (db/hz) 95 85 75 65 55 45 Microphone B Peak SPL (db)= 91.6 (exp 95.6) 35 PSD (db/hz) 95 85 75 65 55 45 35 Receiver / Microphone position Microphone A Peak SPL (db)= 92.5 (exp 93.7) 25 20 200 2000 Frequency DES Literature_CFD Literature_Experiment PSD (db/hz) 25 20 200 2000 Frequency 95 85 75 65 55 45 35 DES Literature_CFD Literature_Experiment Microphone C Peak SPL (db)= 88.5 (exp 92.7) 25 20 200 Frequency 2000 DES Literature_CFD Literature_Experiment Slide 27
Summary Flow over cylinder at Re 3900 using URANS, DES and LES Strouhal number at vertical height of 70D away from the cylinder= 0.196 (exp 0.193); OSPL = 83.6 db (exp83.8 db) Directivity pattern of Δp rms of receivers around the cylinder exemplify dipole sound propagation characteristics Trends of DES predicted Reynolds stresses were in relative good agreement with experimental results URANS & LES had tendency to under predict the magnitude of the principal components of the Reynolds stresses Flow over cylinder at Re 46,000 using DES Fundamental Strouhal number = 0.2 (exp 0.19) at frequency of 1455.8 Hz SPL at vertical height of 70D away from = 92 db (exp 91dB) Directivity pattern of Δp rms of receivers around the cylinder exemplify dipole sound propagation characteristics Trends of the Reynolds stresses are typical to that of a turbulent wake Slide 28
Summary Flow over tandem cylinder at Re 1.66E5 DES Bi-stable flow states at critical cylinder spacing captured Flow between cylinder switches between constant shedding and intermittent shedding modes Near field strouhal number at cylinder surface = 0.203 and far field = 0.213(exp 0.232) Trends of DES predicted surface pressure distribution were in relative good agreement with experimental results Good farfield OASPL agreement with experiment at respective microphone locations. Microphone A = 92.5 (exp 93.7) Microphone B = 91.6 (exp 95.6) Microphone C = 88.5 (exp 92.7) Directivity pattern of Δp rms of receivers around the cylinder exemplify dipole sound propagation characteristics Slide 29