cccccccccccccccccccccccccccccccccccccccccccccccccccccccccccccccc
c      VARIABLES GUIDE
cccccccccccccccccccccccccccccccccccccccccccccccccccccccccccccccc

c      ncells: number of cells
c      nribst: total ribs
c      nribss: in semi-wing
c      cencell: with of central cell

c      rib(i,j) rib i parameter j:

c      rib(i,1) rib number
c      rib(i,2) x_rib
c      rib(i,3) y_LE
c            j=4 y_TE
c            j=5 chord
c            j=6 x'
c            j=7 z_rib
c            j=8 alpha washin calulated in cases 1,2
c            j=9 beta
c            j=10 rotation point
c            j=11 vent in
c            j=12 vent out
c            j=14 open=1 closed=0
c            j=15 anchors number
c            j=16 A %
c            j=17 B %
c            j=18 C %
c            J=19 D %
c            j=20 E %
c            j=21 F % brake
c            j=22 cell width (i to i+1)
c            j=23 extrados length
c            j=24 intrados width
c            j=25 intrados length
c            j=26 inlet length
c            j=30 panel length to the left of rib i - extrados
c            j=31 rib i length - extrados
c            j=32 panel length to the right of rib i - extrados
c            j=33 panel length to the left of rib i - intrados
c            j=34 rib i length - intrados
c            j=35 panel length to the right of rib i - intrados
c            j=36,37,38,39 mark amplification coeficients

c      rib(i,40) rib extrados partial length
c      rib(i,41) rib extrados partial length
c      rib(i,42) rib extrados partial length
c      rib(i,43) rib left intrados partial length
c      rib(i,44) rib intrados partial length
c      rib(i,45) rib right intrados partial length

c      rib(i,50) rib z displacement

c      rib(i,51) washin angle set manually in matrix
c      rib(i,55) Rib relative weight (1.0)

c      rib(i,56) if 0 then rib no rotation in "ss" class (Pampa)
c                is also % of minirib in not "ss" paragliders

c      jcve(i) , jcvi(i) j control miniribs extra - intra

c      rib(i,60) Extrados minirib length
c      rib(i,61) Intrados minirib length

c      rib(i,66) A lenght from TE
c      rib(i,67)
c      rib(i,68)
c      rib(i,69)
c      rib(i,70) E lenght from TE

c      rib(i,80) longitud zona ndif rib i
c      rib(i,79) longitud zona ndif rib i-1
c      rib(i,81)=rib(i,80)-rib(i,79))*xndif
c      rib(i,82)

c      rib(i,90)=rib(i,31)-rib(i,30)  left differences rib-panel extra
c      rib(i,92)=rib(i,31)-rib(i,32)  right differences rib-panel extra
c      rib(i,93)  intra
c      rib(i,95)  intra

c      rib(i,96) Leading egde segment unformated (extra)
c      rib(i,97) Leading edge segment formated (extra)
c      rib(i,98) Leading egde segment unformated (intra)
c      rib(i,99) Leading edge segment formated (intra)


c      rib(i,102) Length from TE to point "2" in V-ribs
c      rib(i,104) Length from TE to point "4" in V-ribs
c      rib(i,105) Length from TE to point "11" in V-ribs
c      rib(i,106) Length from last "11" to equidistant point
c      rib(i,107) Length between "j_121" and equist point
c      rib(i,108) Lolcal length segment (j-1_121,j_121)


c      do klz=1,rib(i,15)
c      rib(i,110+klz) u coordinate anchor klz
c      rib(i,120+klz) v coordinate anchor klz
c      rib(i,130+klz) distance TE to anchor klz along rib contour


c      rib(i,148) airfoil thickness abs
c      rib(i,149) airfoil thickness %

c      rib(i,150) Lextrados middle rib i-1 to i
c      rib(i,151) Lvent
c      rib(i,152) Lintrados middle rib i-1 to i
c      rib(i,150) Lextrados panel i-1 (i-1 to i)
c      rib(i,151) 
c      rib(i,152) Lintrados panel i-1 (i-1 to i

c      rib(i,160) Standard thickness
c      rib(i,165) Vent glue value 
c      rib(i,166) Type-1 Jonc group in rib 1  (???)
       rib(i,167) Jonc length



       rib(i,190) rib extra i
       rib(i,191) panel extra left i
       rib(i,192) rib extra i+1
       rib(i,193) panel extra right i
       rib(i,194) k 191/190
       rib(i,195) k 193/192
       rib(i,196) rib intra i
       rib(i,197) panel intra left i
       rib(i,198) rib intra i+1
       rib(i,199) panel intra right i
       rib(i,200) k 197/196
       rib(i,201) k 199/198

       rib(i,250) Rot_z (geometry matrix)
       rib(i,251) Pos_z (geometry matrix)



c      alpha: airfoil washin angle
c      alpham: max washin
c      beta: airfoil vertical angle
c      calag: calage
c      cple: center of pressure
c      hcp: height pilote - center of pressure
c      assiette:angle between horizontal line and chord
c      finesse: glide ratio
c      aoa: angle of attack AoA
c      nomair(i): airfoil archive

c      np(i,1) airfoil points number
c      np(i,2) airfoil extrados points number 
c      np(i,3) airfoil inlet points number 
c      np(i,4) airfoil intrados points number
c      np(i,5)=np(i,2)+np(i,3)-1 extrados+inlets
c      np(i,6) j nose point (0,0) 

c      u(i,j,20) v(i,j,20): airfoils coordinates
c        K = 1 = original coordinates
c            2 = 100*coordinates
c            3 = scaled coordinates
c            4 = washin coordinates
c            5 = espace coordinates
c            6 = singular points
c                j=1 A anchor point 3D
c                j=2 B anchor point 3D
c                j=3 C anchor point 3D
c                j=4 D anchor point 3D
c                j=5 E anchor point 3D
c                j=6 F anchor point - brake 3D
c                j=7 B intake in point 3D
c                j=8 B intake out point 3D
                 j=10 Nose "j" number
c            7 = overwide local left
c            8 = overwide local right
c            9 = coordinates overwide left
c            10 = coordinates overwide right
c            11 = coordinates left sewing border
c            12 = coordinates right sewing border
c            14 = panel extreme points left
c            15 = panel extreme points right
c            16 = airfoil borders
c            17 = anchor washin coordinates
c            18 = anchor space coordinates
c            19 = anchor absolute coordinates
c            24 = panel extreme corner left
c            25 = panel extreme corner right
c            30 =
c            33 =
c
c            43 = intermediate unloaded airfoil i-1 i scaled c

c            47 = space airfoil (u,v,w) in i
c            48 = intermediate space airfoil between i-1 and i
c            49 = ovalized intermediate space airfoil between i-1 and i

       anccount(i,k)  anchor "j" count in loop J=1,np(i,1)

c      x(i,j) y(i,j) z(i,j): absolute airfoil coordinates
c      xx(1,j) yy(1,j) zz(1,j): central airfoil (or i=0)
c      hol(100,20,20) airfoil holes properties
c      xl(i,j) xr(i,j) panels length
c      skin(k,j) skin tension
c      xupp, xupple, xuppte
c      xlow, xlowle, xlowte, xrib sewing allowances


c      mc(ii,j,k) suspension matrix
c           ii = line plan
c           j = path number
c           k = matrix column
c               1 ramifications number of the path
c               2 1 (ramification level 1)
c               3 order in the level 1
c               4 2 (ramification level 2)
c               5 order in the level 2
c               6 3 (ramification level 3)
c               7 order in the level 3
c               8 4 (ramification level 4)
c               9 order in the level 4
c               10 anchor line (1=A,2=B,3=C,4=c,5=D,6=freno)
c               11 anchor rib number

c               14 Final row
c               15 Final rib

                31 Line type level 1
                32 Line type level 2
                33 Line type level 3
                34 Line type level 4
                35 Line type level 5 (no used)

c      cam(ii) paths in plan ii
c      slp suspension line plans

c      slpi(1), slpi(2), slpi(3)... inici plans

c      corda(i,k) ramification properties of line i
c           k = 1 line plan
c           k = 2 line level (1=riser)
c           k = 3 liner order (in the same level, and left to right)
c           k = 4 action points associated
c           k = 5 path ramifications
c           k = 6 final anchor row 1=A 2=B ...
c           k = 7 anchor rib number

c      cordam nombre de línies individuals

c      xcorda(i,1)  Punt de linia inicial 1
c      ycorda(i,1)
c      xcorda(i,1)
c      xcorda(i,2)  Punt de linia final 2
c      ycorda(i,2)
c      xcorda(i,2)
c      xcorda(i,3)  Punt de linia objectiu 3
c      ycorda(i,3)
c      xcorda(i,3)

c       ii=corda(i,1)

c      x1line(ii,2,corda(i,3))=xcorda(i,1)
c      y1line(ii,2,corda(i,3))=ycorda(i,1)
c      z1line(ii,2,corda(i,3))=zcorda(i,1)   
c      x2line(ii,2,corda(i,3))=xcorda(i,2)
c      y2line(ii,2,corda(i,3))=ycorda(i,2)
c      z2line(ii,2,corda(i,3))=zcorda(i,2)


c      x1line(corda(i,1),corda(i,2),corda(i,3)) line i initial x-coordinate
c      y1line(corda(i,1),corda(i,2),corda(i,3)) line i initial y-coordinate
c      z1line(corda(i,1),corda(i,2),corda(i,3)) line i initial z-coordinate
c      x2line(corda(i,1),corda(i,2),corda(i,3)) line i final x-coordinate
c      y2line(corda(i,1),corda(i,2),corda(i,3)) line i final y-coordinate
c      z2line(corda(i,1),corda(i,2),corda(i,3)) line i final z-coordinate
c      x3line(corda(i,1),corda(i,2),corda(i,3)) line i action point x-coordinate
c      y3line(corda(i,1),corda(i,2),corda(i,3)) line i action point y-coordinate
c      z3line(corda(i,1),corda(i,2),corda(i,3)) line i action point z-coordinate

c      xline(i) line i length
c      raml(i,j) ramfication lengths

c	ln1 line name level
c	ln2 line name letter (A,B,C,...)
c	ln3 line name order or rib
c	ln4(500) line label name
c
c      atp wing type "ds" "ss" "pc"
c      
c      kaa 1: not move nose triangle in "ss"
c      kaa 0: rotate all triangles including nose
c
c      seprix: separació entre ribs X (350)
c      sepriy: separació entre ribs y (90)
c      xwf: wing factor scale
c      xkf: draw factor scale
c
c      uextra(i,l) reformated extrados i in lmax points
c      vextra(i,l) reformated extrados i in lmax points
c      uintra(i,l) reformated intrados i in lmax points
c      vintra(i,l) reformated intrados i in lmax points
c      lmax=jcontroli-jcontrolf+2
c      
c      u(i,j,3) coordinate x control point in rib i
c      v(i,j,3)
c   
*****************************************************************
c      HV-ribs variables:
***************************************************************** 
c      hvr(k,kk) HV-rib data
c            kk=2 rib type
c            kk=3 rib number
c            kk=4 row number
c            ...
c            kk=10 parameter
******************************************************************

       (point "k" are 2,3,4... according schema anchor point "3"
c      ucnt(i,ii,k) coordinate "u" cinta rib i, row ii, point k
c      vcnt(i,ii,k) coordinate "v" cinta rib i, row ii, point k
c
c      ucnt1(i,ii,j) coordinate local j, line 1 (left)
c      vcnt1(i,ii,j) 

c      ucnt2(i,ii,j) coordinate local j, line 2 (center)
c      vcnt2(i,ii,j)  
c
c      ucnt3(i,ii,j) coordinate local j, line 3 (right)
c      vcnt3(i,ii,j) 
c
c      jcon(i,ii,2)  "j" count point by interpolate "2" point
c      jcon2(i,ii,2) "j" count point by interpolate first "2" point

c      rx1(i,j,ii) coordenada linia 1 per aplanar (i-1)
c      ry1(i,j,ii)
c      rz1(i,j,ii)
c      rx2(i,j,ii) coordenada linia 2 per aplanar (i)
c      ry2(i,j,ii)
c      rz2(i,j,ii)
c      rx3(i,j,ii) coordenada linia 3 per aplanar (i+1)
c      ry3(i,j,ii)
c      rz3(i,j,ii)
c
c      xru(2),xrv(2) punts recta "r"
c      xsu(2),xsv(2) punts recta "s"
c      xtu,xtv r-s intersection (subroutine)
c
c      xtu2(i),xtv2(i),xtu4(i),xtv4(i)
c      xtu9(i),xtv9(i),xtu11(i),xtv11(i) points in full diagonal ribs
       
       px9o(j) py9o(j) auxiliar coordinates in V-ribs full (planar)       
       xsegment lenght of line "1-9" of V-rib leading edge
       angle    angle to rotate V-rib 
       angle2   angle to displace V-rib (right)

       extremal lengths for V-ribs full
       xte11(100),xte3(100),xle1(100),xle9(100)


       rib(i,90)=rib(i,31)-rib(i,30) "cut" in left side
       rib(i,92)=rib(i,31)-rib(i,30) "extend" in right side
       xirl(i)
       jirl(i) point j where init reformat in left side
       xirr(i)
       jirr(i) point j where init reformat in right side


       typepoint
                1 = euclidean point
                2 = circle

       typevent
                1 = tree points
                2 = two points
                3 = segment
                4 = double segment

       typetab
                1 = tree points
                2 = 
                3 = triangle

       typejonc

       typeref  1 = romano
                2 = diode

       lyname(1) = default
       lyname(2) = cut_external
       lyname(3) = sewing_line
       lyname(4) = points
       lyname(5) = circles
       lyname(6) = triangles
       lyname(7) = squares
       lyname(8) = text
       lyname(9) = refer

       Section 20: Marks
       gname character*50 generalname
       marks types and parameters paper printer
       typm1(i),typm2(i),typm3(i)
       marks types and parameters MC/Laser
       typm4(i),typm5(i),typm6(i) 

       Section 24: 2D DXF options
       iccolor(1) A lines
       iccolor(5) E
       iccolor(6) F

       Section 25: 3D DXF options
       iccolor(11) A lines
       iccolor(15) E
       iccolor(16) F
       ele3d(11)  ele3dc(11)  >>> 1/0  color extrados
       ele3d(12)  ele3dc(12)  >>> 1/0  color intrados
       ele3d(13)  ele3dc(13)  >>> 1/0  color vents

       Section 28:
       nriser28 number of risers
       p28(i) i=1,2,3,4,5 position % of 5 risers
       a128 angle for max speed (negative)
       n128 number of steps
       a228 angle for max trim (positive)
       n228 number of steps
      
       Section 30:
       rib(i,160) thickness rib amplification

       Section 31: New skin tension
       ksk, ng, ngskt, nribini, nribfin, npoints, ntype
       skinew(20,10), skinnew(0:100,20,10)

       Section 27:
       alc1, alc2  angles last cell in degrees clockwise


       Section 29:

       k29d  Data control
       kgroup  Number of groups
       ncuts(kgroup) Number of cuts
       cutamp(kgroup) cut effect amplification

       rib(i,169) group ng for 3D-shaping

       yhaut: vertical distance for parts separation


       Parameters for part separation:
       panel_x_coe	1.0
       panel_x_min	1.0
       panel_y_coe	1.0
       rib_x_coe	1.0
       rib_y_coe	1.0


       SECTION 33

       x33(i) riser i lenght


       SECTION 34: LINES TABLE

       tylinea(i,1) r or c
       tyline(i,2)  diameter1
       tyline(i,3)  diameter2
       tylinea(i,4) label
       tyline(i,5)  breaking load daN
       tylinea(i,6) material
       tyline(i,7)  weight g/m
       tylinea(i,8) s (sewing) or p (splice)
       tyline(i,9)  total loop cm

       SECTION 35: Solve equilibrium

        k35d        solve=1

        x35ro       air density 
        x35s        projected surface (m2)

	x35V        11.0  m/s  estimated flow speed
	x35Alpha    8.0   deg  estimated wing angle of attact at trim speed
	x35Cl       0.5        wing lift coefficient
	x35Cd	 0.2        wing drag coefficient
	x35Cm       0.1        wing moment coefficient
	x35DLines   0.11  m2   1.0	1
        x35clines
        x35slines	
	x35Dpilot	 0.50  m2   1.0   
        x35cpilot
        x35spilot
	x35Mw       4.0   kg   wing mass
	x35Mp       83.0  kg   pilot mass included harness and instruments
	x35Ml       0.35  kg   1  lines mass
	x35Ycp      0.53  cm   y-coordinate center of pressure
	x35Zcp     -0.25  cm   z-coordinate center of pressure

	x35lift
        x35drag
        x35drage
        x35dinduced
        x35

	x35gamma
	x35theta
	x35GR

	x35ycp
	x35zcp
	x35calage
	x35pp   plumb point
	x35gy
	x35gz
	x35gly
	x35glz

	x35mpilot
	x35mwing
	x35mlines
	x35mtotal



	icase_lines 0 = use default properties
	icase_lines 1 = use table properties

        neven=0 --> odd cells number
        neven=1 --> even cells number

        nsegments --> stl transverse sections

        chord_pcdg estimated mass center % of a typical section (0% leading edge, 100% trailing edge)

        wcdgx3d --> wing center of mass
        wcdgy3d
        wcdgz3d

        scdgx3d --> suspensions lines center of mass
        scdgy3d         
        scdgz3d 

        iflag_assiette --> if set to 1, forced assiette
	assiette2003 --> forced assiette angle, related to special code 2003
