Rapidly Sheared Compressible Turbulence: Characterization of Different Pressure Regimes and Effect...
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![Page 1: Rapidly Sheared Compressible Turbulence: Characterization of Different Pressure Regimes and Effect of Thermodynamic Fluctuations Rebecca Bertsch Advisor:](https://reader037.fdocuments.us/reader037/viewer/2022103022/56649d2f5503460f94a06a14/html5/thumbnails/1.jpg)
Rapidly Sheared Compressible Turbulence: Characterization of Different Pressure Regimes and Effect of Thermodynamic
Fluctuations
Rebecca Bertsch
Advisor: Dr. Sharath GirimajiMarch 29, 2010
Supported by: NASA MURI and Hypersonic Center
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Outline
• Introduction• RDT Linear Analysis of Compressible
Turbulence– Method– 3-Stage Evolution of Flow Variables – Evolution of Thermodynamic Variables– Effect of Initial Thermodynamic Fluctuations
• Conclusions
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Progress
• Introduction• RDT Linear Analysis of Compressible
Turbulence– Method– 3-Stage Evolution of Flow Variables – Evolution of Thermodynamic Variables– Effect of Initial Thermodynamic Fluctuations
• Conclusions
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Motivation• Compressible stability, transition, and turbulence
plays a key role in hypersonic flight application.
• Hypersonic is the only type of flight involving flow-thermodynamic interactions.
• Crucial need for understanding the physics of flow-thermodynamic interactions.
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Application
BackgroundNavier-Stokes
Bousinessq approach
ARSM reduction
Second moment closure
LES
Sub-grid Modeling RANS Modeling
DNS
Decreasing Fidelity of Approach
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ARSM reduction
2-eqn. ARSM
Averaging Invariance
Application
7-eqn. SMC
Transport Processes
Linear Pressure
Effects: RDT
Nonlinear pressure effects
Spectral and dissipative processes
2-eqn. PANS
Navier-Stokes Equations
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Objectives
1. Verify 3-stage evolution of turbulent kinetic energy (Cambon et. al, Livescu et al.)
2. Explain physics of three stage evolution of flow parameters
3. Investigate role of pressure in each stage of turbulence evolution
4. Investigate dependence of regime transitions
*Previous studies utilized Reynolds-RDT, current study uses more appropriate Favre-RDT.
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Progress
• Introduction• RDT Linear Analysis of Compressible
Turbulence– Method– 3-Stage Evolution of Flow Variables – Evolution of Thermodynamic Variables– Effect of Initial Thermodynamic Fluctuations
• Conclusions
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Inviscid Conservation Equations
(Mass)
(Momentum)
(Energy)
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Reynolds vs. Favre-averagingApproach R-RDT(Previous work)
Easier
F-RDT(Current Study)
More appropriate for compressible flow
Averaging Unweighted: Weighted:
Moments 2nd order: 3rd order:
# of PDEs 25 64
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Decomposition of variables
Substitutions:
Mass`
Momentum
Energy
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Mean field Governing Eqns.
Mass
Mom.
Energy
Apply averaging principle and decompose density
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Path to Fluctuating Field Eqns.
• Subtract mean from instantaneous• Apply homogeneity condition(shear flow only)
• Apply linear approximations.
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Mass
Mom.
Energy
Linear F-RDT Eqns. for Fluctuations
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Physical to Fourier Space
• Easier to solve in Fourier space• Apply Fourier transform to variables
• PDEs become ODEs
xti
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Mass
Momentum
Energy
Evolution of
Homogeneous shear flow eqns.
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Final moment equations
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Important ParametersInput Gradient Mach number
Turbulent Mach Number
Temperature Fluctuation Intensity
Output Turbulent Kinetic Energy
Turbulent Polytropic Coefficient
Equi-partition Function
Timescales Shear time
Acoustic time
Mixed time
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Validation- b12 Anisotropy Component DNS R-RDT
F-RDT
ijji
ij k
uub
31
2
""
Good overall agreement
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Validation- KE Growth Rate DNS R-RDT
F-RDT
dtdk
Sk1
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Progress
• Introduction• RDT Linear Analysis of Compressible
Turbulence– Method– 3-Stage Evolution of Flow Variables – Evolution of Thermodynamic Variables– Effect of Initial Thermodynamic Fluctuations
• Conclusions
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Three-stage Behavior: Shear Time
Peel-off from burger’s limit clear; shows regime transition.*Verification of behavior found in Cambon et. al.
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Status Before Current Work
• Validation of method and verification of previous results complete.
• New investigations of three-stage physics follows.
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Three-stage Behavior: Acoustic Time
Three-stages clearly defined; final regime begins within 2-3 acoustic times.*Acoustic timescale first presented in Lavin et al.
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Three-stage Behavior: Mixed Time
Three-stages clearly defined; onset of second regime align.
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Regimes of Evolution
• Regime 1:
• Regime 2:
• Regime 3:
gMSt 2~0
312~ 0 atM g
3at
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Evolution of Gradient Mach NumberShear time aligns 1st regime, constant Mg value.
Mg(t) reaches 1 by 1 acoustic time regardless of initial value.
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Evolution of Turbulent Mach Number
First regime over by 4 shear times.
Second regime aligns in mixed time.
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Three Regime Physics: Regime 1
Pressure plays an insignificant role in 1st regime.
)(rijij
ji Pdt
uud
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Three Regime Physics: Regime 1
Zero pressure fluctuations.
Dilatational and internal energy stay at initial values.
No flow-thermodynamic interactions.
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Three Regime Physics: Regime 2
Pressure works to nullify production in 2nd regime.
)(rijij
ji Pdt
uud
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Three Regime Physics: Regime 2Pressure fluctuations build up.
Dilatational K. E. and I. E. build up.
Equi-partition is achieved as will be seen later.
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Three Regime Physics: Regime 3
Rapid pressure strain correlation settles to a constant value
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Three Regime Physics: Regime 3
Production nearly insensitive to initial Mg value.
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Three Regime Physics: Regime 3
• Energy growth rates nearly independent of Mg.
• p’(total) =p’(poisson) + p’(acoustic wave).
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Three-regime conclusions
• Regime 1: Turbulence evolves as Burger’s limit; pressure insignificant.
• Regime 2: Pressure works to nullify production; turbulence growth nearly zero.
• Regime 3: Turbulence evolves similar to the incompressible limit.
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Progress
• Introduction• RDT Linear Analysis of Compressible
Turbulence– Method– 3-Stage Evolution of Flow Variables – Evolution of Thermodynamic Variables– Effect of Initial Thermodynamic Fluctuations
• Conclusions
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Polytropic Coefficient
R-RDT F-RDT
n≈γ according to DNS with no heat loss (Blaisdell and Ristorcelli)
F-RDT preserves entropy, R-RDT does not
2
2
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''
ppp
n
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Progress
• Introduction• RDT Linear Analysis of Compressible
Turbulence– Method– 3-Stage Evolution of Flow Variables – Evolution of Thermodynamic Variables– Effect of Initial Thermodynamic Fluctuations
• Conclusions
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KE: Initial Temperature Fluctuation
Initial temperature fluctuations delay onset of second regime.
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KE: Initial Turbulent Mach Number
KE evolution influenced by initial Mt only weakly
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Equi-Partition Function: Initial Temperature Fluctuation
Dilatational energy maintains dominant role longer.
0"2
"2~~2 TTc
uu
v
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Equi-Partition Function: Initial Turbulent Mach Number
Balance of energies nearly independent of initial Mt value
0"2
"2~~2 TTc
uu
v
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Regime 1-2 Transition
Initial Temperature fluctuation
Initial Turbulent Mach number
1st transition heavily dependent on temperature fluctuations
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Regime 2-3 Transition
Initial Temperature fluctuation
Initial Turbulent Mach number
2nd transition occurs within 4 acoustic times regardless of initial conditions
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Initial fluctuations conclusions
• Turbulence evolution heavily influenced by temperature fluctuations.
• Velocity fluctuations weakly influence flow.• Regime 1-2 transition delayed by temperature
fluctuations.• Regime 2-3 transition occurs before 4
acoustic times.
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Progress
• Introduction• RDT Linear Analysis of Compressible
Turbulence– Method– 3-Stage Evolution of Flow Variables – Evolution of Thermodynamic Variables– Effect of Initial Thermodynamic Fluctuations
• Conclusions
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Conclusions• F-RDT approach achieves more accurate results than R-
RDT.• Flow field statistics exhibit a three-regime evolution
verification.• Role of pressure in each role is examined:
– Regime 1: pressure insignificant– Regime 2: pressure nullifies production– Regime 3: pressure behaves as in incompressible limit.
• Initial thermodynamic fluctuations have a major influence on evolution of flow field.
• Initial velocity fluctuations weakly affect turbulence evolution.
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Contributions of Present Work
1. Explains the physics of three-stages.
2. Role of initial thermodynamic fluctuations quantified.
3. Aided in improving to compressible turbulence modeling.
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References1. S. B. Pope. Turbulent Flows. Cambridge University Press, 2000.
2. G. K. Batchelor and I. Proudman. "The effect of rapid distortion of a fluid in turbulent motion." Q. J. Mech. Appl. Math. 7:121-152, 1954.
3. C. Cambon, G. N. Coleman and D. N. N. Mansour. "Rapid distortion analysis and direct simulation of compressible homogeneous turbulence at finite Mach number." J. Fluid Mech., 257:641-665, 1993.
4. G. Brethouwer. "The effect of rotation on rapidly sheared homogeneous turbulence and passive scalar transport, linear theory and direct numerical simulations." J. Fluid Mech., 542:305-342, 2005.
5. P.A. Durbin and O. Zeman. "Rapid distortion theory for homogeneous compressed turbulence with application to modeling." J. Fluid Mech., 242:349-370, 1992.
6. G. A. Blaisdell, G. N. Coleman and N. N. Mansour. "Rapid distortion theory for compressible homogeneous turbulence under isotropic mean strain." Phys. Fluids, 8:2692-2705, 1996.
7. G. N. Coleman and N. N. Mansour. "Simulation and modeling of homogeneous compressible turbulence under isotropic mean compression." in Turbulent Shear Flows 8, pgs. 269-282, Berlin:Springer-Verlag, 1993
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References cont.
8. L. Jacquin, C. Cambon and E. Blin. "Turbulence amplification by a shock wave and rapid distortion theory." Phys. Fluids A, 5:2539, 1993.
9. A. Simone, G. N. Coleman and C. Cambon. "The effect of compressibility on turbulent shear flow: a rapid distortion theory and direct numerical simulation study." J. Fluid Mech., 330:307-338, 1997.
10. H. Yu and S. S. Girimaji. "Extension of compressible ideal-gas RDT to general mean velocity gradients." Phys. Fluids 19, 2007.
11. S. Suman, S. S. Girimaji, H. Yu and T. Lavin. "Rapid distortion of Favre-averaged Navier-Stokes equations." Submitted for publication in J. FLuid Mech., 2009.
12. S. Suman, S. S. Girimaji and R. L. Bertsch. "Homogeneously-sheared compressible turbulence at rapid distortion limit: Interaction between velocity and thermodynamic fluctuations."
13. T. Lavin. Reynolds and Favre-Averaged Rapid Distortion Theory for Compressible, Ideal Gas Turbulence}. A Master's Thesis. Department of Aerospace Engineering. Texas A \& M University. 2007.
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Questions…