ebcs_vol2seg.F File Reference

#include "implicit_f.inc"

Go to the source code of this file.

Functions/Subroutines
subroutine	ebcs_vol2seg (nseg, surf_nodes, iseg, segvar, a, v, x, volmon, fsav)

Function/Subroutine Documentation

ebcs_vol2seg()

subroutine ebcs_vol2seg	(	integer	nseg,
		integer, dimension(nseg,4)	surf_nodes,
		integer, dimension(nseg)	iseg,
		type(t_segvar)	segvar,
			a,
			v,
			x,
			volmon,
			fsav )

Definition at line 31 of file ebcs_vol2seg.F.

C-----------------------------------------------
C   M o d u l e s
C-----------------------------------------------
      USE segvar_mod
      USE ale_mod
C-----------------------------------------------
C   I m p l i c i t   T y p e s
C-----------------------------------------------
#include      "implicit_f.inc"
C-----------------------------------------------
C   D u m m y   A r g u m e n t s
C-----------------------------------------------
      INTEGER NSEG,ISEG(NSEG),SURF_NODES(NSEG,4)
      my_real
     .        a(3,*),x(3,*),v(3,*),volmon(*),fsav(*)
      TYPE(t_segvar) :: SEGVAR
C-----------------------------------------------
C   L o c a l   V a r i a b l e s
C-----------------------------------------------
      INTEGER IS,K,KSEG,SEGAD,IRECT(4)
      my_real orient,
     .        pext,pres,vol,ro,en,
     .        fac,x13,y13,z13,x24,y24,z24,nx,ny,nz,s,
     .        vn1,vn2,vn3,vn4,vel,vn,vplus,vmoins,
     .        gam1,gamrp,vcrt2,fluxm,fluxe,flux,
     .        gv,rv,rsr,pn,enin,roin,enou,roou,pns,fx,fy,fz,
     .        gam,norm,dmin,dmou,hin,hou,pna
      my_real pna1,pna2,pna3,pna4,rsr1,rsr2,rsr3,rsr4,aire
C=======================================================================
C VOLUME MONITORE
      gam   =volmon(1)
      pext  =volmon(3)
      pres  =volmon(12)
      vol   =volmon(16)
      ro    =volmon(20)/vol
C volumetric Energy
      en    =volmon(13)/vol
C massic Enthalpy
      hin   = (en+pres)/ro
 
      gam1 = one/(gam-one)
      gamrp= half*(gam-one)/gam
      vcrt2= two*gam*pres/ro/(gam+one)
 
      flux =zero
      fluxm=zero
      fluxe=zero
      aire =zero
 
      DO is=1,nseg
        DO k=1,4
          irect(k)=surf_nodes(is,k)
        ENDDO
        IF(irect(4) == 0) THEN
          irect(4)=irect(3)
          fac=third
        ELSE
          fac=fourth
        ENDIF
C
C INDICES FOR SEGMENTS, AND OREINTATIONS
C
        kseg=abs(iseg(is))
        orient=float(iseg(is)/kseg)
 
C NORMAL VECTORS
        x13=x(1,irect(3))-x(1,irect(1))
        y13=x(2,irect(3))-x(2,irect(1))
        z13=x(3,irect(3))-x(3,irect(1))
        x24=x(1,irect(4))-x(1,irect(2))
        y24=x(2,irect(4))-x(2,irect(2))
        z24=x(3,irect(4))-x(3,irect(2))
        nx=y13*z24-z13*y24
        ny=z13*x24-x13*z24
        nz=x13*y24-y13*x24
        norm=sqrt(nx*nx+ny*ny+nz*nz)
        s=half*norm
        IF(norm>em20)THEN
          norm=orient/norm
          nx=nx*norm
          ny=ny*norm
          nz=nz*norm
        ENDIF
        
 
C NORMAL VELOCITIES
c        write(6,*)iseg(is),nx,ny,nz
        vn1=v(1,irect(1))*nx+v(2,irect(1))*ny+v(3,irect(1))*nz
        vn2=v(1,irect(2))*nx+v(2,irect(2))*ny+v(3,irect(2))*nz
        vn3=v(1,irect(3))*nx+v(2,irect(3))*ny+v(3,irect(3))*nz
        vn4=v(1,irect(4))*nx+v(2,irect(4))*ny+v(3,irect(4))*nz
        IF(irect(4) == irect(3))THEN
          vn=fac*(vn1+vn2+vn3)
        ELSE
          vn=fac*(vn1+vn2+vn3+vn4)
        ENDIF
        vplus =max(vn,zero)
        vmoins=min(vn,zero)
C
C STAGNATION POINT
C
        vel=min(vn1,zero)**2
        vel=min(vel,vcrt2)
        gv=gamrp*ro*vel/pres
        IF(gv>em4)THEN
         rsr    = (one-gv)**gam1
         pna1     = pres*rsr**gam
        ELSE
         rv     = half*ro*vel
         rsr    = one - rv/(pres*gam)
         pna1     = pres - rv
        ENDIF
        rsr1=rsr
C
        vel=min(vn2,zero)**2
        vel=min(vel,vcrt2)
        gv=gamrp*ro*vel/pres
        IF(gv>em4)THEN
         rsr    = (one-gv)**gam1
         pna2     = pres*rsr**gam
        ELSE
         rv     = half*ro*vel
         rsr    = one - rv/(pres*gam)
         pna2     = pres - rv
        ENDIF
        rsr2=rsr
C
        vel=min(vn3,zero)**2
        vel=min(vel,vcrt2)
        gv=gamrp*ro*vel/pres
        IF(gv>em4)THEN
         rsr    = (one-gv)**gam1
         pna3     = pres*rsr**gam
        ELSE
         rv     = half*ro*vel
         rsr    = one - rv/(pres*gam)
         pna3     = pres - rv
        ENDIF
        rsr3=rsr
C
        vel=min(vn4,zero)**2
        vel=min(vel,vcrt2)
        gv=gamrp*ro*vel/pres
        IF(gv>em4)THEN
         rsr    = (one-gv)**gam1
         pna4     = pres*rsr**gam
        ELSE
         rv     = half*ro*vel
         rsr    = one - rv/(pres*gam)
         pna4     = pres - rv
        ENDIF
        rsr4=rsr
C
        IF(irect(4) == irect(3))THEN
          pna=fac*(pna1+pna2+pna3)
          rsr=fac*(rsr1+rsr2+rsr3)
        ELSE
          pna=fac*(pna1+pna2+pna3+pna4)
          rsr=fac*(rsr1+rsr2+rsr3+rsr4)
        ENDIF
C INCOMING FLOW
        enin = pna*gam1
        roin = rsr*ro
C        ROIN =RO
C        ENIN =EN
C OUTGOING FLOW
        segad=ale%GLOBAL%NVCONV*(kseg-1)
        roou = segvar%RHO(kseg)
        enou = segvar%EINT(kseg)
 
        segvar%RHO(kseg)=roin
        segvar%EINT(kseg)=enin
C
C MASS FLUX AND ENTHALPY TO AIRBAGS (>0 si rentrant)
C airbag -> fluid 
C hin  =  (Ea+Pa)/roa 
C fluide -> airbag 
C hou = (Ef+P)/rof +1/2 v+^2
C        HOU=(ENOU+PNA)/ROOU+0.5*VPLUS**2
c
        hou=gam*enou/roou+half*vplus**2
        dmin=roin*vmoins
        dmou=roou*vplus        
        aire =aire +s
        flux =flux +s*vn
        fluxm=fluxm+s*(dmou+dmin)
        fluxe=fluxe+s*(hin*dmin+hou*dmou)
 
C RELATIVE PRESSURE
        pn  = pna1-pext
        pns=-pn*s*fac
        fx=pns*nx
        fy=pns*ny
        fz=pns*nz
 
        a(1,irect(1))=a(1,irect(1))+fx
        a(2,irect(1))=a(2,irect(1))+fy
        a(3,irect(1))=a(3,irect(1))+fz
 
        pn  = pna2-pext
        pns=-pn*s*fac
        fx=pns*nx
        fy=pns*ny
        fz=pns*nz
        a(1,irect(2))=a(1,irect(2))+fx
        a(2,irect(2))=a(2,irect(2))+fy
        a(3,irect(2))=a(3,irect(2))+fz
 
        pn  = pna3-pext
        pns=-pn*s*fac
        fx=pns*nx
        fy=pns*ny
        fz=pns*nz
        a(1,irect(3))=a(1,irect(3))+fx
        a(2,irect(3))=a(2,irect(3))+fy
        a(3,irect(3))=a(3,irect(3))+fz
 
        IF(irect(4)/=irect(3))THEN
        pn  = pna4-pext
        pns=-pn*s*fac
        fx=pns*nx
        fy=pns*ny
        fz=pns*nz
          a(1,irect(4))=a(1,irect(4))+fx
          a(2,irect(4))=a(2,irect(4))+fy
          a(3,irect(4))=a(3,irect(4))+fz
        ENDIF
 
      ENDDO
 
       volmon(22)=volmon(22) - fluxe
       volmon(24)=volmon(24) - fluxm
       flux=-flux+fsav(9)*fsav(8)
       fsav(8)=fsav(8)      + aire
       fsav(9)=flux/fsav(8)
C-----------
      RETURN