1. Towards robust and accurate computations of shock/turbulence interactions Johan Larsson Center for Turbulence Research Stanford University Queen’s University, Nov 13, 2007

2. Outline Flows of interest and potential applications The SciDAC program and my work Numerical challenges in shock/turbulence interaction The proposed hybrid method Evaluation and verification of the method Summary, the next steps, and some ideas for the future Note -- I’m assuming some familiarity with: Numerical solution of PDEs -- finite difference methods Fluid mechanics -- shock waves and turbulence Feel free to interrupt!

3. Problems of interest Flows with interactions between turbulence, shock waves, and material interfaces occur in a wide range of interesting applications Super/hypersonic flight, shock/boundary layer interaction, inertial confinement fusion (ICF), supernovae explosions, scramjet combustion, shock wave lithotripsy,… Turbulent mixing of two fluids with different densities (Rayleigh-Taylor instability) E.g. early stages of supernova explosion, late stages of ICF Source: Andy Cook, LLNL

4. Problems of interest X-43 (Mach 9.6) Scramjet Source: www.tipmagazine.com Source: www.dfrc.nasa.gov/Gallery

5. Problems of interest Shock wave passing through a cylinder of heavier gas, generating vorticity and mixing (Richtmeyer-Meshkov instability) E.g. scramjet combustion (shock interacting with injected fuel) Source: Andy Cook, LLNL

6. Problems of interest Supernovae explosions -- natural convection, shock waves, combustion (fusion) The turbulent infalling gas starts shaking the core, causing it to pulsate… the oscillations are so intense they send out sound waves. The waves exert a pressure that expels material, reinforcing the shock wave created by the star's collapse. They also amplify the core's vibrations in a runaway reaction, says Burrows, "until the star finally explodes." National Geographic, March 2007, on supernovae: Source: flash.uchicago.edu

7. The SciDAC program Dept of Energy ‘Scientific Discovery through Advanced Computing’ Multi-disciplinary program to advance ‘peta-scale’ computational science Computer science -- MPI, filesystems, visualization, etc Applied mathematics -- scalable algorithms, etc Science -- climate, quantum mechanics, numerical relativity, astrophysics, biology, etc Our project Stanford, NASA Ames, Lawrence Livermore, UCLA Initial focus -- numerical methods for shock/turbulence/material interface interactions This talk is about my part of this project

8. shock isotropic turbulence Working roadmap Hybrid numerical method Existing methods capture shocks well, but sacrifice accuracy in treating turbulence -- core problem is numerical dissipation Proposed method largely eliminates this numerical dissipation Verify method on a sequence of problems Increase complexity step by step Canonical shock/turbulence interaction study Unanswered questions of flow physics Basic problem for shock/turbulence modeling This talk will cover the first 2 items

9. Introduction -- governing equations Navier-Stokes equations for a perfect gas Convective terms (LHS) contain amazing range of physics Shock waves -- discontinuities in the flow field Vortex stretching etc -- energy transfer towards smaller eddies Convective terms also pose greatest numerical challenge Special ‘shock-capturing’ schemes needed for shocks Numerical energy transfer (aliasing errors) often cause blow-up

10. Introduction -- capturing of shock waves Shock thickness is roughly the molecular mean-free-path (1 nm in air) Unfeasible to resolve numerically Shock-capturing -- get the correct ‘jump’ on a realistic grid Need nonlinear (solution-dependent) dissipation Need conservative form of convective terms -- proven to give correct weak solution Conservative and non-conservative forms:

11. Introduction -- capturing broadband turbulence Stability affected by aliasing error: The energy is ‘aliased’ to some unphysical wavenumber Could lead to catastrophic energy growth and numerical instability Linear, ‘dealiasing’ dissipation Split form of convective terms -- reduces aliasing error

12. The Taylor-Green vortex (3D) Idealized vortex-stretching for nearly incompressible flow No shock waves, but large aliasing errors Note instability of conservative form, stability of split form Note effect on bandwidth: 1/3, 1/2, 2/3 of maximum wavenumber Energy spectra at t=5Kinetic energy evolution

13. Introduction -- contradictory requirements Need conservative form and shock-capturing dissipation for shocks Conservative form => need dealiasing dissipation for stability Dissipation harms accuracy -- only 1/3 or 1/2 of wavenumbers accurate ‘Unified’ methods -- same scheme everywhere Conservative, both types of dissipation E.g. hyperviscosity (Cook, PoF 2007), WENO (Martin et al, JCP 2006) ‘Hybrid’ methods -- different schemes around and away from shocks Can use split form for ‘turbulence’ => non-dissipative Issues of conservation and stability at the interface, where to use each scheme With upwinding (Adams and Shariff, JCP 1996), filtering (Rizzetta et al, AIAA J 2001), central (Pantano et al, JCP 2007)

14. Hybrid method -- general approach Concept: different numerics for different physics Minimal dissipation through split form Novelties in present method: Conservative coupling for general split schemes Stability proof at the interface (JCP, under review) Numerical grid

15. Hybrid method -- numerical flux framework Conservation at interfaces by numerical flux form with defined Hybridize by Have reduced problem of interface conservation to finding

16. Hybrid method -- WENO scheme Adaptively chosen weighted combination of candidate fluxes Weights chosen based on smoothness Candidate stencils and sample weights State-of-the-art for shock-capturing, but expensive and dissipative for turbulence

17. Hybrid method -- central split scheme Split convective form by Ducros et al (JCP 2000) Derive bilinear interpolation stencils for flux form such that yields split form by Ducros et al

18. Hybrid method -- shock sensor Must find regions of shock waves robustly Many sensors possible, and area in need of improvement Currently based on comparing dilatation and vorticity Dilatation -- small in turbulence, large negative at shocks Vorticity -- large in turbulence, small at shocks Then set

19. Hybrid method -- final details Use 8th order central scheme / 5th order WENO scheme 4th order Runge-Kutta scheme in time 8th order scheme for viscous terms Compare results to ‘Pure’ WENO -- 7th order WENO everywhere Hybrid + 8th order ‘dealiasing’ dissipation of form Hybrid with 2nd order central scheme

20. Test cases -- verification and illustration of method 3D Taylor-Green problem Verify accuracy and stability for broadband ‘turbulence’ Illustrate adverse effect of numerical dissipation 1D shock/entropy interaction Verify shock-capturing and hybrid concept 2D shock/vorticity/entropy interaction Verify method on idealized interaction with shockwave 3D isotropic decaying turbulence with shocklets Verify accuracy for compressible turbulence Provide inflow condition for full shock/turbulence case

21. The Shu-Osher shock/entropy interaction in 1D Mach 3 shock moves into entropy wave, interaction amplifies entropy waves and creates acoustic waves WENO confined to shock waves No numerical noise at interfaces -- evidence of stability Hybrid method less dissipative than pure WENO Entropy profiles

22. 2D shock/vorticity/entropy interaction at Mach 1.5 Oblique vorticity and entropy waves interacting with a normal shock Amplification of vorticity and kinetic energy by shock Compared to linear theory -- 5th order convergence for amplification ratio (order of the shock-capturing scheme) Contours of vorticityVorticity amplification

23. Isotropic decaying turbulence Initial conditions: Large enough to spontaneously generate shocklets (weak shocks) Shock-sensor finds these appropriately Dilatation flatness much larger than 3 good measure of shocklets Contours of dilatation

24. Isotropic decaying turbulence Compare on 64^3 grid with filtered DNS on 256^3 Shock-capturing dissipation (pure WENO) overly dissipative Linear 8th order dissipation same thing, but less severely Dissipation more important than order of accuracy Kinetic energy decayVorticity decay

25. Isotropic decaying turbulence Accurate bandwidth: 1/4, 1/2, 2/3 of maximum wavenumber Similar to the inviscid Taylor-Green vortex Note: addition of explicit subgrid-scale model would only make this worse Velocity spectraDilatation spectra

26. Summary Numerical dissipation has negative effect on the accuracy for broadband turbulence -- decreases accurate bandwidth by factor of 2 or more Would need 8 times more grid points for equivalent accuracy Dissipation larger than ideal subgrid-scale model -- should not evaluate models with dissipative numerics Hybrid approach allows for minimal dissipation by use of split form Introduces additional complications, but increased accuracy worth the ‘price’ Side-benefit of speed -- central scheme 5 times faster than WENO Overall robust, accurate, and efficient -- good framework for future DNS and LES studies Order of accuracy less important -- at least for turbulence statistics, and for these problems

27. Future work Shock sensor How to find shocks robustly for more general flows? How to parallelize a hybrid method efficiently? The expensive WENO scheme is used locally, in ‘random’ portions of the domain -- load balancing non-trivial Canonical shock/turbulence interaction at high Mach and Reynolds numbers How to limit the size of the inflow database? shock isotropic turbulence

28. Some interesting research topics Modeling of shock/turbulence interaction in large eddy simulation Mathematically unresolved shock waves are no different than unresolved turbulence -- can/should they be modeled jointly/analogously? Why are split convective terms more nonlinearly robust? Two partial explanations exist, neither is complete 30 years of numerical evidence -- there must be a reason… Shock identification Structure of the velocity gradient tensor? Jumps in entropy?

29. Some interesting research topics NASA X-43 achieved Mach 9.6 with scramjet engine in 2004 Better understanding and modeling of shock/turbulence interactions and induced mixing of fuel and oxidizer needed to design better scramjets Heat load on high-speed vehicles depend on the transition to turbulence Discovery shuttle in 2005 -- ground control could not predict the transition point (Annu. Rev. Fluid Mech. 2006) Experiments on inertial confinement fusion are ongoing Mixing induced by shock/turbulence interactions can severely degrade the fusion process (indeed prevent it completely)

30. Acknowledgements Financial support NSERC Postdoctoral Fellowship US Department of Energy SciDAC program Center for Turbulence Research Stimulating discussions Many people, including Sanjiva Lele, Parviz Moin, Bertil Gustafsson, Albert Honein, and Andy Cook