TALK=T;RUN(1,1)
  DISPLAY

  MONO-PROPELLANT ROCKET COMBUSTION

  2-dimensional (x-y), Cartesian, steady, two-phase, elliptic
  simulation

  The problem considered is that of the injection of monopropellant
  droplets through small holes in one end of a rocket motor. These
  droplets burn (i.e undergo a phase change involving the
  disappearance of high-density liquid and its replacement by low-
  density gas), at a rate dependent upon the droplet diameter. As a
  consequence, a pressure gradient is set up which accelerates the
  gas and, to a lesser extent, the liquid. Friction between the
  droplets and the gas causes the former at first to deccelerate and
  later to accelerate.

  The model is highly idealised, and does not represent any
  particular motor or propellant.

  You will have an opportunity to vary the interphase-friction
  coefficient and the injection velocity of the liquid.

  enddis
  PHOTON USE
  p
  phi


  gr ou z 1
  set vec comp
  au1 cv1 -
  msg Gas-velocity vectors
  vec z 1 sh
  msg Press  to continue
  pause
  vec off;red
  set vec comp
  bu2 dv2 -
  msg Droplet-velocity vectors
  vec z 1 sh
  msg Press  to continue
  pause
  vec off;red
  msg volume fraction of liquid
  con liq z 1 sh;int 50
  msg Press  to continue
  pause
  msg Note that the grid is very coarse
  gr z 1
  msg Press e to END
  enduse
  DISPLAY
  The problem considered is that of the injection of monopropellant
  droplets through small holes in one end of a rocket motor. These
  droplets burn (i.e undergo a phase change involving the dis-
  appearance of high-density liquid and its replacement by low-
  density gas), at a rate dependent upon the droplet diameter. As a
  consequence, a pressure gradient is set up which accelerates the
  gas and, to a lesser extent, the liquid. Friction between the
  droplets and the gas causes the former at first to deccelerate
  and later a accelerate.
  The main task is to compute the distance from the injector at
  which the propellant is fully consumed, as functions: of the
  injection velocity, of the propellant and combustion-product
  properties, and of a measure of the relative speed of momentum
  and heat transfer.
  The GX-subroutine GXDROP is used for this case.
  ENDDIS
 ************************************************************
  Group 1. Run Title and Number
 ************************************************************
 ************************************************************
 
 TEXT(Rock2; 2D MONOPROPELLANT ROCKET   :W971 )
 
 ************************************************************
 ************************************************************
 
 IRUNN = 1 ;LIBREF = 14
 ************************************************************
  Group 2. Time dependence
 STEADY = T
 ************************************************************
  Group 3. X-Direction Grid Spacing
 CARTES = T
 NX = 10
 XULAST =1.
 XFRAC(1)=0.1 ;XFRAC(2)=0.2
 XFRAC(3)=0.3 ;XFRAC(4)=0.4
 XFRAC(5)=0.5 ;XFRAC(6)=0.6
 XFRAC(7)=0.7 ;XFRAC(8)=0.8
 XFRAC(9)=0.9 ;XFRAC(10)=1.
 ************************************************************
  Group 4. Y-Direction Grid Spacing
 NY = 10
 YVLAST =0.5
 YFRAC(1)=0.1 ;YFRAC(2)=0.2
 YFRAC(3)=0.3 ;YFRAC(4)=0.4
 YFRAC(5)=0.5 ;YFRAC(6)=0.6
 YFRAC(7)=0.7 ;YFRAC(8)=0.8
 YFRAC(9)=0.9 ;YFRAC(10)=1.
 ************************************************************
  Group 5. Z-Direction Grid Spacing
 PARAB = F
 NZ = 1
 ZWLAST =1.
 ZFRAC(1)=1.
 ************************************************************
  Group 6. Body-Fitted Coordinates
 ************************************************************
  Group 7. Variables: STOREd,SOLVEd,NAMEd
 ONEPHS = F
 EQUVEL = F
 NAME(1)=P1 ;NAME(3)=AU1
 NAME(4)=BU2 ;NAME(5)=CV1
 NAME(6)=DV2 ;NAME(9)=GAS
 NAME(10)=LIQ ;NAME(11)=SHAD
 NAME(149)=CFIP ;NAME(150)=MDOT
    * Y in SOLUTN argument list denotes:
    * 1-stored 2-solved 3-whole-field
    * 4-point-by-point 5-explicit 6-harmonic averaging 
 SOLUTN(P1,Y,Y,N,N,N,Y)
 SOLUTN(AU1,Y,Y,N,N,N,Y)
 SOLUTN(BU2,Y,Y,N,N,N,Y)
 SOLUTN(CV1,Y,Y,N,N,N,Y)
 SOLUTN(DV2,Y,Y,N,N,N,Y)
 SOLUTN(LIQ,Y,Y,N,N,N,Y)
 SOLUTN(SHAD,Y,Y,N,N,N,Y)
 SOLUTN(CFIP,Y,N,N,N,N,Y)
 SOLUTN(MDOT,Y,N,N,N,N,Y)
 INTMDT = 150
 ************************************************************
  Group 8. Terms & Devices
    * Y in TERMS argument list denotes:
    * 1-built-in source 2-convection 3-diffusion 4-transient
    * 5-first phase variable 6-interphase transport         
 TERMS(P1,Y,Y,Y,N,Y,Y)
 TERMS(AU1,Y,Y,N,Y,Y,Y)
 TERMS(BU2,Y,Y,N,Y,N,Y)
 TERMS(CV1,Y,Y,Y,Y,Y,Y)
 TERMS(DV2,Y,Y,Y,Y,N,Y)
 TERMS(LIQ,Y,Y,N,Y,N,Y)
 TERMS(SHAD,Y,Y,N,Y,N,Y)
 DIFCUT =0.5 ;ZDIFAC =1.
 GALA = F ;ADDDIF = F
 EQDVDP = F
 ISOLX = -1 ;ISOLY = -1 ;ISOLZ = -1
 ************************************************************
  Group 9. Properties used if PRPS is not
  stored, and where PRPS = -1.0 if it is!
 RHO1 =10. ;TMP1 =0.
 EL1 =0.
 TSURR =0. ;TEMP0 =0.
 PRESS0 =1.0E+07
 DVO1DT =0. ;DRH1DP =0.
 EMISS =0. ;SCATT =0.
 RADIA =0. ;RADIB =0.
 RHO2 =1.0E+04 ;TMP2 =0.
 EL2 =0.
 DVO2DT =0. ;DRH2DP =0.
 ENUL =1.0E-05 ;ENUT =0.
 PHINT(AU1)=-2.022E+04 ;PHINT(BU2)=-2.022E+04
 PHINT(CV1)=-2.022E+04 ;PHINT(DV2)=-2.022E+04
 PHINT(LIQ)=-2.022E+04 ;PHINT(SHAD)=-2.022E+04
 PRNDTL(CV1)=1. ;PRNDTL(DV2)=1.
 PRT(CV1)=1. ;PRT(DV2)=1.
 CP1 =1. ;CP2 =1.
 ************************************************************
  Group 10.Inter-Phase Transfer Processes
 CFIPS = GRND1
 RLOLIM =1.0E-09 ;CMDOT =1.
 CFIPA =0. ;CFIPB =0.
 CFIPC =1.0E+05 ;CFIPD =0.
 CINT(P1)=1. ;CINT(AU1)=1.
 CINT(BU2)=1. ;CINT(CV1)=1.
 CINT(DV2)=1. ;CINT(LIQ)=1.
 CINT(SHAD)=1.
 PHINT(P1)=-2.022E+04 ;PHINT(AU1)=-2.022E+04
 PHINT(BU2)=-2.022E+04 ;PHINT(CV1)=-2.022E+04
 PHINT(DV2)=-2.022E+04 ;PHINT(LIQ)=-2.022E+04
 PHINT(SHAD)=-2.022E+04
 ************************************************************
  Group 11.Initial field variables (PHIs)
 FIINIT(P1)=1.0E-10 ;FIINIT(AU1)=50.
 FIINIT(BU2)=50. ;FIINIT(CV1)=1.0E-10
 FIINIT(DV2)=1.0E-10 ;FIINIT(GAS)=0.999
 FIINIT(LIQ)=1.0E-03 ;FIINIT(SHAD)=1.0E-03
 FIINIT(CFIP)=1.0E-10 ;FIINIT(MDOT)=10.
   No PATCHes yet used for this Group
 INIADD = F
 FSWEEP = 1
 NAMFI =CHAM
 ************************************************************
  Group 12. Patchwise adjustment of terms
  Patches for this group are printed with those
  for Group 13.
  Their names begin either with GP12 or &
 ************************************************************
  Group 13. Boundary & Special Sources
 
 PATCH(INLET ,WEST , 1, 1, 1, 5, 1, 1, 1, 1)
 COVAL(INLET ,AU1 ,0. ,0. )
 COVAL(INLET ,BU2 ,0. ,50. )
 COVAL(INLET ,CV1 ,0. ,0. )
 COVAL(INLET ,DV2 ,0. ,0. )
 COVAL(INLET ,GAS , FIXFLU ,0. )
 COVAL(INLET ,LIQ , FIXFLU ,2000. )
 
 PATCH(OUTLET ,CELL , 10, 10, 1, 5, 1, 1, 1, 1)
 COVAL(OUTLET ,AU1 ,0. ,0. )
 COVAL(OUTLET ,BU2 ,0. ,0. )
 COVAL(OUTLET ,GAS ,1. ,0. )
 COVAL(OUTLET ,LIQ ,1000. ,0. )
 XCYCLE = F
 EGWF = T
 WALLCO = GRND2
 ************************************************************
  Group 14. Downstream Pressure For PARAB
 ************************************************************
  Group 15. Terminate Sweeps
 LSWEEP = 200 ;ISWC1 = 1
 LITHYD = 1 ;LITFLX = 1 ;LITC = 1 ;ITHC1 = 1
 ISWR1 = 1 ;ISWR2 = 10000
 SELREF = T
 RESFAC =1.0E-02
 ************************************************************
  Group 16. Terminate Iterations
 LITER(P1)=20 ;LITER(AU1)=10
 LITER(BU2)=10 ;LITER(CV1)=10
 LITER(DV2)=10 ;LITER(LIQ)=1
 LITER(SHAD)=1
 ENDIT(P1)=1.0E-03 ;ENDIT(AU1)=1.0E-03
 ENDIT(BU2)=1.0E-03 ;ENDIT(CV1)=1.0E-03
 ENDIT(DV2)=1.0E-03 ;ENDIT(LIQ)=1.0E-03
 ENDIT(SHAD)=1.0E-03
 ************************************************************
  Group 17. Relaxation
 RELAX(P1,LINRLX,1.)
 RELAX(AU1,FALSDT,0.02)
 RELAX(BU2,FALSDT,0.02)
 RELAX(CV1,FALSDT,2.0E-03)
 RELAX(DV2,FALSDT,2.0E-03)
 RELAX(GAS,LINRLX,1.)
 RELAX(LIQ,LINRLX,0.2)
 RELAX(SHAD,LINRLX,0.6)
 RELAX(CFIP,LINRLX,1.)
 RELAX(MDOT,LINRLX,1.)
 OVRRLX =0.
 EXPERT = F ;NNORSL = F
 ************************************************************
  Group 18. Limits
 VARMAX(P1)=1.0E+10 ;VARMIN(P1)=-1.0E+10
 VARMAX(AU1)=1.0E+06 ;VARMIN(AU1)=-1.0E+06
 VARMAX(BU2)=1.0E+06 ;VARMIN(BU2)=-1.0E+06
 VARMAX(CV1)=1.0E+06 ;VARMIN(CV1)=-1.0E+06
 VARMAX(DV2)=1.0E+06 ;VARMIN(DV2)=-1.0E+06
 VARMAX(GAS)=1. ;VARMIN(GAS)=1.0E-06
 VARMAX(LIQ)=1.0E-03 ;VARMIN(LIQ)=1.0E-09
 VARMAX(SHAD)=1. ;VARMIN(SHAD)=1.0E-06
 VARMAX(CFIP)=1.0E+10 ;VARMIN(CFIP)=-1.0E+10
 VARMAX(MDOT)=1.0E+10 ;VARMIN(MDOT)=-1.0E+10
 ************************************************************
  Group 19. Data transmitted to GROUND
 PRTSIZ = T
 PARSOL = F
 ISG62 = 1
 ************************************************************
  Group 20. Preliminary Printout
 ************************************************************
  Group 21. Print-out of Variables
 INIFLD = F ;SUBWGR = F
    * Y in OUTPUT argument list denotes:
    * 1-field 2-correction-eq. monitor 3-selective dumping      
    * 4-whole-field residual 5-spot-value table 6-residual table
 OUTPUT(P1,Y,N,Y,Y,Y,Y)
 OUTPUT(AU1,Y,N,Y,Y,Y,Y)
 OUTPUT(BU2,Y,N,Y,Y,Y,Y)
 OUTPUT(CV1,Y,N,Y,Y,Y,Y)
 OUTPUT(DV2,Y,N,Y,Y,Y,Y)
 OUTPUT(GAS,N,N,N,N,N,N)
 OUTPUT(LIQ,Y,N,Y,Y,Y,Y)
 OUTPUT(SHAD,Y,N,Y,Y,Y,Y)
 OUTPUT(CFIP,Y,N,Y,N,N,N)
 OUTPUT(MDOT,Y,Y,Y,Y,Y,Y)
 ************************************************************
  Group 22. Monitor Print-Out
 IXMON = 5 ;IYMON = 1 ;IZMON = 1
 NPRMON = 100000 ;NPRMNT = 1 ;TSTSWP = -1
 UWATCH = T ;USTEER = T
 HIGHLO = F
 ************************************************************
  Group 23.Field Print-Out & Plot Control
 NPRINT = 100000 ;NUMCLS = 5
 NXPRIN = 0 ;IXPRF = 1 ;IXPRL = 10000
 NYPRIN = -1 ;IYPRF = 1 ;IYPRL = 10000
 IPLTF = 1 ;IPLTL = -1 ;NPLT = 1
 ISWPRF = 1 ;ISWPRL = 100000
 ITABL = 1 ;IPROF = 1
 ABSIZ =0.5 ;ORSIZ =0.4
 NTZPRF = 1 ;NCOLPF = 50
 ICHR = 2 ;NCOLCO = 45 ;NROWCO = 20
 
 PATCH(XPROFILE,PROFIL, 1, 10, 1, 1, 1, 1, 1, 1)
 PLOT(XPROFILE,AU1 ,-1. ,-1. )
 PLOT(XPROFILE,BU2 ,-1. ,-1. )
 PLOT(XPROFILE,LIQ ,0. ,0. )
 PLOT(XPROFILE,SHAD,0. ,0. )
 
 PATCH(XPROFIL2,PROFIL, 1, 10, 1, 1, 1, 1, 1, 1)
 PLOT(XPROFIL2,CFIP,0. ,0. )
 PLOT(XPROFIL2,MDOT,0. ,0. )
 ************************************************************
  Group 24. Dumps For Restarts
 SAVE = T ;NOWIPE = F
 NSAVE =CHAM
STOP