This subdirectory provides the Database files for the nominal Mach 8.9 Hypersonic Turbulent axisymmetric Hollow Cylinder/Flare
 experiment conducted by Williams at the Imperial College Gun Tunnel.  It was conducted with N2 as the working fluid.

Included in the database are data from a fully separated case generated by a 36 degree Flare
 positioned at 720 mm from the cylinder leading edge.

 The experiments were reported in:

Experimental Data Source Document is 
     Murray, N., Hillier, R. and Williams, S.
     Axisymmetric Hypersonic Shock-Wave/Turbulent Boundary-Layer Interactions
     Journal of Fluid Mechanics, Vol. 714, Jan. 2, 2013, pp. 152-189.

Also, see
     Williams, N.
     Three-Dimensional Separation of a Hypersonic Boundary-Layer
     PhD. Thesis, Department of Aeronautics, Imperial College of Science, Technology and Medicine
     University of London, 2004.

     Murray, N.
     Three-Dimensional Turbulent Shock-Wave/Boundary-Layer Interactions in Hypersonic Flows
     PhD. Thesis, Department of Aeronautics, Imperial College of Science, Technology and Medicine
     University of London, 2007.

     Murray, N. and Hillier, R.
     Separated Shock Wave/Turbulent Boundary Layer Interactions at Hypersonic Speeds
     AIAA Paper 2006-3038, June 2006.

     Mallinson, S.G., Hillier, R., Jackson, A.P., Kirk, D.C. Soltani, S. and Zanchetta, M.
     Gun tunnel flow calibration: defining input conditions for hypersonic flow computations
     Shock Waves, Vol. 10, pp. 313-322, 2000.

     Mallinson, S.G., Hillier, R., Zanchetta, Soltani, S. and Kirk, D.
     An Experimental and Numerical Study of Hypersonic Turbulent Boundary Layer Flows
     AIAA Paper 1997-2290, 1997.

CFD computations for this case are previously unpublished and were done by James.L.Brown@NASA.Gov
     using DPLR Real-Gas/Navier-Stokes code.

     For related work see Appendix B2, also:
     Brown, J.L.
     Shock-Wave Impingement on Boundary Layers at Hypersonic Speeds: Computational Analysis and Uncertainty
     AIAA Paper 2011-3141, 42nd AIAA Thermophysics Conference, Honolulu, Hawaii, June 27-30, 2011.

     Brown, J.L.
     Hypersonic Shock Wave Impingement on Turbulent Boundary Layers: Computational Analysis and Uncertainty
     Journal of Spacecraft and Rockets, Vol. 50, No. 1, Jan-Feb 2013, pp 96-123.
     ../../X.Extras/Publications/JSR2013Vol50No1pp96_123_JLBrown.pdf
     ../../X.Extras/Publications/JSR2013Vol50No1_JLBrownFigures:

     Note the diverging freestream inlet BC for these CFD solutions is based on the papers of Mallinson listed above.
     A cell-face centered pointwise BC (e.g. Hillier.pbca listed in these subdirectories) is applied at the inlet face
      of the computational domain for these DPLR computations consistent with Fig 6 of Mallinson, et al. by means of the
      program BCFaceGen.f (also listed in these subdirectories) rather than a uniform freestream.

Subdirectory Structure is as follows:
     A.CompressionCornerCases
         A6.WilliamsCylFlare
            A6.0.ReadmeWilliams.txt ... This file
            A6.1.ExperimentDataFiles
              AuthorFiles ... Files sent from Experimentor, file formats may vary
                  HeatFlare36degrees
                  PressuredFlare36degrees
                  Williams.xls
 DataBase---> TecplotASCII ... Data converted to standard database ASCII Tecplot format
                     WilliamsFlare36.dat
                     WilliamsCylFlare.png
            A6.2.CFDFiles
                     Williams.free
                     WilliamsFlare36.p3da     ... grid using ASCII plot3d format
                     fconV402.248Blk.inp      ... DPLR input for grid conversion program fconvert
                     run.fconvert             ...  script to run DPLR fconvert
                     BCFaceGen.f
                        Note BCFaceGen.F generates to the pointwise BC at the inlet face of the computational domain,
                        see Williams.pbca
                     Williams.pbca            ... DPLR pointwise boundary condition file (from BCFaceGen) for Williams case
                     Williams.inp             ... DPLR input deck for Williams case
                     surf.dat                 ... DPLR Solution (surface properties) ... Tecplot ASCII data file
                     voldb.dat.bz2            ... DPLR Solution (field variables) ... Tecplot ASCII data file
                     PWilliamsTMX.png
                     QWilliamsTMX.png
                     REDWOOD2.pbs ... pbs script to run DPLR for Williams case

Also see cylinder centerbody data files and solutions from B2.MurrayHillier subdirectory, as the Mallinson Hollow Cylinder is the test surface shared by the two experiments of Murray and of Williams.


