Unsteady Supersonic flow over parabolic 20% bump

D 1 September 2011

Case description

20% bump in a channel
inviscid flow
unsteady upstream Mach number (sinusoidal oscillation from 3 to 2.4 to 3.)

MACH=3.+.6*(cos((t-.1)*6.28)-1.)*step((t-.1)*(1.1-t))

Numerical parameters

1600x320 quad mesh
morphing functions are

MORPH_X = 5*X MORPH_Y = Y+step(1-(sqr(x-.4)/0.04))*(1-sqr(x-.4)/0.04)*.2*(1-Y)
2nd order explicit Runge-Kutta, CFL=1
HLLC scheme, MUSCL extrapolation, 3rd order Kim limiter

Results

Ressources

An example of parameter file (main.rpm):

BLOCK:PROJECT      

  NZONE     = 1       

  COORD     = 2D      

  TIME      = UNSTEADY 

  !RESIDUALS = 1.e-8

  DURATION  = 2.

  NCYCLE    = 100

ENDBLOCK               



BLOCK:OUTPUT       

  FORMAT = VTK-BIN

  FILE   = "C2"

  PERIOD = 1 

ENDBLOCK



BLOCK:ZONE       

  NAME   = "" 

  SOLVER = EULER  

ENDBLOCK



BLOCK:MESH

  FORMAT = INTERNAL

  FILE   = "quad200x40.tym" 

  MORPH_X = 5*X

  MORPH_Y = Y+step(1-(sqr(x-.4)/0.04))*(1-sqr(x-.4)/0.04)*.2*(1-Y)

ENDBLOCK



BLOCK:MODEL

  DYNAMICS = EULER

  GAS      = AIR

ENDBLOCK



BLOCK:TIME_PARAM 

  METHOD    = RK2

  CFL       = 1.

  RESIDUALS = .1

ENDBLOCK



BLOCK:SPAT_PARAM 

  SCHEME   = HLLC

  HIGHRES  = MUSCL

  LIMITER  = ALBADA

ENDBLOCK



BLOCK:INIT

  P        = 1.0E5

  T        = 300.

  MACH     = 3.

  DIRECTION = (1., 0., 0.)

ENDBLOCK



BLOCK:BOCO

  FAMILY = IMIN

  TYPE   = SUPERSONIC_INLET

  PI     = 1.E5

  TI     = 300.

  MACH   = 3.+.6*(cos((t-.1)*6.28)-1.)*step((t-.1)*(1.1-t))

  DIRECTION = ( 1., 0., 0.)

ENDBLOCK



BLOCK:BOCO

  FAMILY = IMAX

  TYPE   = SUPERSONIC_OUTLET

ENDBLOCK



BLOCK:BOCO

  FAMILY = JMIN

  TYPE   = SYMMETRY

ENDBLOCK



BLOCK:BOCO

  FAMILY = JMAX

  TYPE   = SYMMETRY

ENDBLOCK

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Unsteady Supersonic flow over parabolic 20% bump

Case description

Numerical parameters

Results

Ressources

An example of parameter file (main.rpm):

Also in this section

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Pages

Unsteady shock Wave / boundary Layer interaction

Multi-element inviscid flow (Suddhoo-Hall)

Hypersonic flow around two cylinders

Shock reflection/diffraction over pyramid

Supersonic reflexion on 10° wedge