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110th AIAA/CEAS Aeroacoustics Conference, Manchester, UK, 10 -12 May, 2004
Refraction Corrections for Surface Integral Methods in Jet Aeroacoustics
FongLoon PanPurdue University, West Lafayette, IN
Ali UzunFlorida State University, Tallahassee, FL
Anastasios LyrintzisPurdue University, West Lafayette, IN
210th AIAA/CEAS Aeroacoustics Conference, Manchester, UK, 10 -12 May, 2004
Outline
Surface Integral Methods– Porous FW-H method
Refraction Corrections– Simple geometric acoustics theory (GA)– Lilley’s equation
Validation (Simple point source)
Application (Jet noise prediction using LES)
Conclusions
310th AIAA/CEAS Aeroacoustics Conference, Manchester, UK, 10 -12 May, 2004
Surface Integral Methods
CFD (near-field) Acoustics far-field
source
Far-fieldobserver
(nonlinear)
(linear)
Surface integral methods
410th AIAA/CEAS Aeroacoustics Conference, Manchester, UK, 10 -12 May, 2004
Porous FW-H Method (Time Domain)
nijiji
o
ii
Sret
r
Sret
r
oL
Sret
noT
noisequadrupole
QLT
uunPL
uU
dSr
LdS
r
L
atxp
dSr
Utxp
txptxptxptxp
ˆ
1),(4
),(4
),(),(),(),(
2'
'
''''
where
510th AIAA/CEAS Aeroacoustics Conference, Manchester, UK, 10 -12 May, 2004
Porous FW-H Method (Frequency Domain)
nUr
S
r
S
rari
oL
S
noariT
LT
L
dSr
LdS
r
Le
a
ixp
dSr
Ueixp
xpxpxp
o
o
ˆ
ˆˆ),(ˆ4
ˆ),(ˆ4
),(ˆ),(ˆ),(ˆ
2/'
/'
'''
and are Fourier transform of Lr and Un
610th AIAA/CEAS Aeroacoustics Conference, Manchester, UK, 10 -12 May, 2004
Jet Noise Predictions• S cannot surround the entire source region• MGB can be used outside S• Refraction corrections (predict zone of silence)
710th AIAA/CEAS Aeroacoustics Conference, Manchester, UK, 10 -12 May, 2004
Simple Geometric Acoustics(GA) Ray Theory (1977)
• Refraction of sound through thick cylindrical shear layer
• Acoustic wavelength < shear layer thickness
• Ray angle & amplitude correction
From Papamochou
810th AIAA/CEAS Aeroacoustics Conference, Manchester, UK, 10 -12 May, 2004
Simple Geometric Acoustics(GA) Ray Theory
coscoso
o
o aU
a
U : the velocity at the downstream end of the control surface : the sound emission angle with respect to the jet axis : the emission angle in the ambient air
o
Asymmetric parallel shear flow
910th AIAA/CEAS Aeroacoustics Conference, Manchester, UK, 10 -12 May, 2004
Lilley’s Equation (1974)
:acoustic pressure fluctuation normalized by :acoustic source distribution :mean flow velocity
where
u
1010th AIAA/CEAS Aeroacoustics Conference, Manchester, UK, 10 -12 May, 2004
Lilley’s Equation
: Green’s function associated to Fourier transformed solution of Lilley’s wave equationxs : source position
1110th AIAA/CEAS Aeroacoustics Conference, Manchester, UK, 10 -12 May, 2004
High-Frequency Asymptotic Approximations
Assumptions:•Distance between source and jet centerline axis is sufficiently large (i.e. several factors of 1/ko), R (ko is streamwise wavenumber, ko = /ao)
Critical azimuthal wavenumber, n can be scaled to the order of ko
i.e. (Asymmetric, high-frequency)
As source moves closer to the jet centerline axis
i.e. (Quasi-symmetric, high-frequency)
1210th AIAA/CEAS Aeroacoustics Conference, Manchester, UK, 10 -12 May, 2004
Lilley’s Approximation Solutions
: reduced Green’s function: free-space Green’s function
1310th AIAA/CEAS Aeroacoustics Conference, Manchester, UK, 10 -12 May, 2004
Asymmetric, Far-field Approximation
where
1410th AIAA/CEAS Aeroacoustics Conference, Manchester, UK, 10 -12 May, 2004
Quasi-symmetric, Far-field Approximation
where
1510th AIAA/CEAS Aeroacoustics Conference, Manchester, UK, 10 -12 May, 2004
Comparisons of asymmetric and symmetric approximations
1610th AIAA/CEAS Aeroacoustics Conference, Manchester, UK, 10 -12 May, 2004
Simple Point Source -ValidationLk = 40rj ; rk = 5rj ; R = 60rj
1710th AIAA/CEAS Aeroacoustics Conference, Manchester, UK, 10 -12 May, 2004
Refraction Corrections for Simple Point Source
1810th AIAA/CEAS Aeroacoustics Conference, Manchester, UK, 10 -12 May, 2004
Mach 0.9, Reynolds Number 400,000 Isothermal Jet LES
• 6-th order compact spatial differencing• 6-th order compact spacial filter• No explicit SGS model• 15.6 million grid points
• Streamwise length 35ro ;width and height 30ro
• 50,000 time steps• 5.5 days of run time using 200 POWER3
processors on an IBM-SP
1910th AIAA/CEAS Aeroacoustics Conference, Manchester, UK, 10 -12 May, 2004
Boundary ConditionsTam & Dong’s radiation boundary conditions
Tam & Dong’s radiation boundary conditions
Tam & Dong’s Radiationbcs
Tam & Dong’s outflow boundary conditions
2010th AIAA/CEAS Aeroacoustics Conference, Manchester, UK, 10 -12 May, 2004
FW-H Control Surface
30rj
7.8rj
2110th AIAA/CEAS Aeroacoustics Conference, Manchester, UK, 10 -12 May, 2004
Jet Mean-Flow Profile
MJ = 0.46A = -0.14B = 0.0044
2210th AIAA/CEAS Aeroacoustics Conference, Manchester, UK, 10 -12 May, 2004
OASPL Results
2310th AIAA/CEAS Aeroacoustics Conference, Manchester, UK, 10 -12 May, 2004
Jet Aeroacoustics• Acoustic data collected every 5 time steps over a
period of 25,000 time steps • Maximum Strouhal numbers resolved (based on
grid spacing) St=3.0• Open surface: shallow angles ( ) not accurate,
since streamwise control surface is relatively short• Closed surface: spurious effects at ( ) due to a
line of dipoles on the outflow surface, as quadrupoles exit the domain
)/14( ox cL
o40
o80
2410th AIAA/CEAS Aeroacoustics Conference, Manchester, UK, 10 -12 May, 2004
Lighthill Code
• Code employs the time derivative formulation of Lighthill’s volume integral
• Uses the time history of the jet flow data provided by the 3-D LES code
• 8th-order accurate explicit scheme to compute the time derivatives
• Cubic spline interpolation to evaluate the source term at retarded times
2510th AIAA/CEAS Aeroacoustics Conference, Manchester, UK, 10 -12 May, 2004
Lighthill Code (continued)
• Time accurate data was saved inside the jet at every 10 time steps over a period of 40,000 time steps
• 1.2 Terabytes (TB) of total data to process
• Used 1160 processors in parallel for the volume integrals
• Cut-off frequency corresponds to Strouhal number 4.0 due to the fine grid spacing inside the jet
)/23( ox cL
2610th AIAA/CEAS Aeroacoustics Conference, Manchester, UK, 10 -12 May, 2004
Animation
• Animation on the next slide shows the time variation of the Lighthill sources that radiate noise in the direction of the observer located at R = 60ro, = 30o on the far-field arc
2710th AIAA/CEAS Aeroacoustics Conference, Manchester, UK, 10 -12 May, 2004
2810th AIAA/CEAS Aeroacoustics Conference, Manchester, UK, 10 -12 May, 2004
OASPL Predictions Using Lighthill Analogy
(deg)
OA
SPL
(dB
)
0 10 20 30 40 50 60 70 80 90 100 110 120100
102
104
106
108
110
112
114
116
118
120
122
Lighthill' s integral until x = 24ro
Lighthill' s integral until x = 28ro
Lighthill' s integral until x = 32ro
LES + FWH open control surface #1exp. of Mollo-Christensen et al. (cold jet)exp. of Lush (cold jet)exp. of Stromberg et al. (cold jet)
2910th AIAA/CEAS Aeroacoustics Conference, Manchester, UK, 10 -12 May, 2004
Conclusions• Simple GA method and Lilley’s equation are
added to the surface integral methods to predict zone of silence
• Jet noise LES results were improved
• GA method is simpler, but does not take azimuthal variation into account
• Lilley’s equation is up to 60 times more expensive
3010th AIAA/CEAS Aeroacoustics Conference, Manchester, UK, 10 -12 May, 2004
The End