Supersonic reflexion on 10° wedge

D 1 June 2010

Case description

Shock reflexion in a channel which section is reduced by a 10° wedge. The upstream flow is Mach 2. One can observe (weak) shock reflexions, an expansion fan and its interaction with shock waves.

(highly refined) First order computation

The computation is fully converged to 6 orders of magnitude (local time stepping with explicit integration method). The numerical scheme is the only first order HLLC.
The mesh has been automatically refined 4 times with SPLIT=ISO-TRI option (459k cells).

Second order SVM computation

The computation is fully converged to 6 orders of magnitude (local time stepping with explicit integration method). The numerical scheme is HLLC with 2nd order SVM extrapolation (without limiters). The original mesh has 1792 triangles; the SVM mesh has 5376 (quad) CV.

Ressources

The mesh is available in the mesh repository.

The parameter file (main.rpm) for SVM computation is

BLOCK:PROJECT  

  NZONE     = 1       

  COORD     = 2D      

  TIME      = STEADY 

  RESIDUALS = 1.e-6

ENDBLOCK               



BLOCK:OUTPUT  

  FORMAT = VTK-BIN       

  FILE   = "SVM2" 

  PERIOD = 1

ENDBLOCK



BLOCK:ZONE    

  NAME   = "wedge10" 

  SOLVER = EULER  

ENDBLOCK



BLOCK:MESH

  FORMAT = CGNS

  FILE   = "channelwedge10tri.cgns"

ENDBLOCK



BLOCK:MODEL

  DYNAMICS = EULER

  GAS      = AIR

ENDBLOCK



BLOCK:TIME_PARAM

  RESIDUALS = 0.5

  DTCALC    = LOCAL_STABILITY_CONDITION 

  CFL       = 0.5

  CFL_MAX   = 1.

ENDBLOCK



BLOCK:SPAT_PARAM  

  SCHEME   = HLLC

  HIGHRES  = SVM

ENDBLOCK



BLOCK:INIT

  PI      = 1.E5

  TI      = 300.

  MACH    = 2.

  DIRECTION = (1., 0., 0.)

ENDBLOCK



BLOCK:BOCO

  FAMILY    = INLET

  TYPE      = SUPERSONIC_INLET

  PI        = 1.E5

  TI        = 300.

  MACH      = 2.

  DIRECTION = (1., 0., 0.)

ENDBLOCK



BLOCK:BOCO

  FAMILY = TOP

  TYPE   = SYMMETRY

ENDBLOCK



BLOCK:BOCO

  FAMILY = BOTTOM

  TYPE   = SYMMETRY

ENDBLOCK



BLOCK:BOCO

  FAMILY = OUTLET

  TYPE   = SUPERSONIC_OUTLET 

ENDBLOCK

Also in this section

Unsteady shock Wave / boundary Layer interaction This is an unsteady viscous computation of a shock tube problem in a closed 1x1 box. The initial conditions are set (...)

Tuesday 19 May 2009

Multi-element inviscid flow (Suddhoo-Hall) This inviscid flow on a multi-element airfoil is interesting since this geometry has been defined through a (...)

Saturday 29 August 2009

Hypersonic flow around two cylinders Case description inviscid flow upstream Mach number 10Numerical Parameters first order HLLC (...)

Saturday 29 August 2009

Shock reflection/diffraction over pyramid Case description An unsteady shock wave (travelling Mach = 2.85) impacts a pyramid obstacle. A first reflexion (...)

Saturday 29 August 2009

Unsteady Supersonic flow over parabolic 20% bump Case description 20% bump in a channel inviscid flow unsteady upstream Mach number (sinusoidal oscillation from 3 (...)

Thursday 1 September 2011

Supersonic reflexion on 10° wedge

Case description

(highly refined) First order computation

Second order SVM computation

Ressources

The parameter file (main.rpm) for SVM computation is

Also in this section

Search

Pages

Unsteady shock Wave / boundary Layer interaction

Multi-element inviscid flow (Suddhoo-Hall)

Hypersonic flow around two cylinders

Shock reflection/diffraction over pyramid

Unsteady Supersonic flow over parabolic 20% bump