1. Shock focusing and Converging Geometries - in the context of the VTF validation D.J.Hill Galcit Nov 1, 2005

2. Simulation Technology (ie the VTF code) – R. Deiterding Computational engine –Parallel 3-D Eulerian AMR framework AMROC with a suite of CFD solvers –Today’s results Van Leer with MUSCL reconstruction & WENO Fluid-solid coupling capability –Level set based –Implementation as Ghost Fluid Method ghost fluid region FLUID SOLID Boundary F UtUt UnUn Interpolation operations – e.g. with solid surface mesh –Mirrored fluid density and velocity values U F M into ghost cells –Solid velocity values U S on facets –Fluid pressure values in surface points (nodes or face centroids)

3. Non-symmetric external wedge An Example of Shocks - complex boundaries and Richtmyer-Meshkov Instability Mach 1.5 shock in Air interacts with a non- symmetric wedge Followed by an SF6 interface Temperature plots with density shadows amroc/weno/applications/euler/2d/Triangle/

4. Existing Experiments: Conical Geometry –Setchel,Strom,Sturtevant -1972 10 degree half angle. Argon at 1.5 Torr Mach 6 shock –Milton, Takayama -1998, Milton et al -1986 10,20,30 degree half angle Mach 2.4, gamma 1.4 –Kumar, Hornug, Sturtevant – 2003 Air-SF6, Mach 1.55 Perturbed interface – RMI. Similar to “Phase 0” - one gas only Two gases with perturbed interface

5. Guderley’s Implosion Problem (1942) Cylindrical or Spherical Shocks Assumptions of Strong Shock (independent of the flow ahead of the shock) Similarity variable: Cp/Cv n (1-n)/n n 5/30.8156250.2260540.6883770.452692 7/50.8352170.1972940.7171730.394364 6/50.8611630.1612200.7571420.320756 Cylindrical Spherical

6. Simulation configuration for Conical shocktube: SSS ‘72 Mach 6 shock Argon (gamma = 5/3, molecular weight 39.9) 10.17 degree half angle Aperture diameter 15.3 cm Probe width 3.22 mm Simulations used analytic levelset with the GFM capability of the VTF Vtf/amroc/clawpack/applications/euler/2d/Conical_Shocktube/ And Vtf/amroc/clawpack/applications/euler/3d/Conical_Shocktube/

7. Experimental Data: Shock speed along centerline Shock speed during convergent phase is measured on the centerline of the cone Normalized by initial shock speed (Mach 6) Speeds over Mach 18 at last measurement Shock speed after reshock is also available for Sturtevant ‘72 From Setchell, Strom and Stutevant –JFM 1972

8. Shock diagram in conical geometry SSS – JFM 1972 Jumps in shock speed correspond to Machstem collisions on the axis of symmetry

9. Axi-Symmetric Flow equations- Can use 2D solver! v u z r Geometric source term Exploit axi-symmetry to simulate the Converging conical geometry. The divergence operator in cylindrical co-ordinates produces a geometric source Advantage: reduction of dimension Disadvantage: loss of conservation

10. Visualization of VTF Conical shocktube simulation Leading shock (blue) and reflected shocks. Plotted as Isosurface of Artificial 3D Schlieren (magnitude of density gradient) colored by density. 90 degree wedge removed for display. Time = 0.0016 sec. Mach 6 shock in Conical shock tube: Plane cut colored by density. Both shock And reshock shown.

11. Validation: Comparison with experiment Shock detection algorithm based on pressure curvature Shock speed calculated from Rankine-Hugoniot jump conditions No real gas corrections, but affects may be important for highest Mach numbers For M=18 (Vs/Vo =3)

12. Comparison of Wedge and Cone Prior to reflection: Density and Pressure t=0.0001 sec --note curved mach-stem In conical case t=0.000165 sec -- conical case far advanced and higher pressures

13. After reflection: t=0.00042 sec

14. ASC converging shock experiments (P. Dimotakis) Phase 0: A single gas is used, the shock interacts with the boundary of the wedge producing shock mach stems, reflected shocks and triple points. The focusing of the shock is achieved by the successive reflection of the shock Phase 1: Two gases are used. The driver gas in the shocktube, and a lens gas in the wedge. The shape of the boundary (contact) between the two gases has been specially designed to curve the shock producing a circular shock centered on the apex of the wedge. P. Dimotakis & R. Samtaney Phase 2: A third gas is used. It is placed within the wedge after the lens. Purturbations on the contact between this gas and the lens gas will give rise to a Richtmyer-Meshkov instability, and the acceleration towards the apex will also have aspects of the Rayleigh-Taylor instability

15. Hinge-plate assembly design and implementation. P.Dimotakis Two plates with sharp leading edges joined by an adjustable hinge –Rounded hinge (1/4″ radius) desingularizes apex and shock rebound Accessible from test-section rear and sides Plates can be angled over a range of 6º – 15º wrt horizontal. –Angles measured to within  0.1  Assembly can be removed with plate angles fixed –Required for membrane replacement in Phase-1 experiments

16. Phase 0  Euler code validation R. Samtaney 0-035  w1 = 14.06   0.21   w2 = 9.94   0.21 

17. Comparison of target experiments Phase 0 and Phase 1 Phase 0 vs Phase 1 Smooth circular shock in produced by Phase 1: no triple points Guderly exponent: n=0.874 Compared with expected: n=0.835

18. Phase 2 Configuration As in the Phase 1 simulations, there is a shocktube gas (gas1) and a lens gas (gas2) related by a density ratio Rho2 / Rho1 = 1.4.Phase 1 In addition to these two gases, there is a target gas inside the wedge (gas3). We take 1.09 gas2 by Rho3/Rho2 = 5. This would be consistent with using Air for the lensing gas and SF6 for the target gas. The extended clawpack solvers were used for this simulation, the input files and code are found in the repository. A base resolution of 250x100 was used with 4 additional levels of refinement (factors 2,2,2,2).input files and code

19. Phase 2 Simulation: Animations of Density With initial perturbations With out Initial perturbations

20. Issues of Interest Boundary Layers: How important are they? –More important during reshock? What is the sensitivity of the Lens design, (Phase 1) to: –Mach Number –Lens shape Need to explore in full 3D simulation using low dissipation method with LES for the mixing zone