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List of variables and their meaning

Table: (continued)
Table 21: Variables in CalculiX.
variable meaning
   
REARRANGEMENT OF THE ORDER IN THE INPUT DECK
ifreeinp next blank line in field inp
ipoinp(1,i) index of the first column in field inp containing information on a block of lines in the input deck corresponding to fundamental key i; a fundamental key is a key for which the order in the input file matters (the fundamental keys are listed in file keystart.f)
ipoinp(2,i) index of the last column in field inp containing information on a block of lines in the input deck corresponding to fundamental key i;
inp a column i in field inp (i.e. inp(1..3,i)) corresponds to a uninterrupted block of lines assigned to one and the same fundamental key in the input deck. inp(1,i) is its first line in the input deck, inp(2,i) its last line and inp(3,i) the next column in inp corresponding to the same fundamental key; it takes the value 0 if none other exists.
MATERIAL DESCRIPTION
nmat # materials
matname(i) name of material i
nelcon(1,i) # (hyper)elastic constants for material i (negative kode for nonlinear elastic constants)
nelcon(2,i) # temperature data points for the elastic constants of material i
elcon(0,j,i) temperature at (hyper)elastic temperature point j of material i
elcon(k,j,i) (hyper)elastic constant k at elastic temperature point j of material i
nrhcon(i) # temperature data points for the density of material i
rhcon(0,j,i) temperature at density temperature point j of material i
rhcon(1,j,i) density at the density temperature point j of material i
nshcon(i) # temperature data points for the specific heat of material i
shcon(0,j,i) temperature at temperature point j of material i
shcon(1,j,i) specific heat at constant pressure at the temperature point j of material i
shcon(2,j,i) dynamic viscosity at the temperature point j of material i
shcon(3,1,i) specific gas constant of material i
nalcon(1,i) # of expansion constants for material i
nalcon(2,i) # of temperature data points for the expansion coefficients of material i
alcon(0,j,i) temperature at expansion temperature point j of material i
alcon(k,j,i) expansion coefficient k at expansion temperature point j of material i
ncocon(1,i) # of conductivity constants for material i
ncocon(2,i) # of temperature data points for the conductivity coefficients of material i
cocon(0,j,i) temperature at conductivity temperature point j of material i
cocon(k,j,i) conductivity coefficient k at conductivity temperature point j of material i
orname(i) name of orientation i
orab(1..6,i) coordinates of points a and b defining the new orientation
norien # orientations
isotropic hardening  
nplicon(0,i) # temperature data points for the isotropic hardening curve of material i
nplicon(j,i) # of stress - plastic strain data points at temperature j for material i
plicon(0,j,i) temperature data point j of material i
plicon(2*k-1,j,i) stress corresponding to stress-plastic strain data point k at temperature data point j of material i
plicon(2*k,j,i) plastic strain corresponding to stress-plastic strain data point k at temperature data point j of material i
kinematic hardening  
nplkcon(0,i) # temperature data points for the kinematic hardening curve of material i
nplkcon(j,i) # of stress - plastic strain data points at temperature j for material i
plkcon(0,j,i) temperature data point j of material i
plkcon(2*k-1,j,i) stress corresponding to stress-plastic strain data point k at temperature data point j of material i
plkcon(2*k,j,i) plastic strain corresponding to stress-plastic strain data point k at temperature data point j of material i
kode=-1 Arrudy-Boyce
-2 Mooney-Rivlin
-3 Neo-Hooke
-4 Ogden (N=1)
-5 Ogden (N=2)
-6 Ogden (N=3)
-7 Polynomial (N=1)
-8 Polynomial (N=2)
-9 Polynomial (N=3)
-10 Reduced Polynomial (N=1)
-11 Reduced Polynomial (N=2)
-12 Reduced Polynomial (N=3)
-13 Van der Waals (not implemented yet)
-14 Yeoh
-15 Hyperfoam (N=1)
-16 Hyperfoam (N=2)
-17 Hyperfoam (N=3)
-50 deformation plasticity
-51 incremental plasticity (no viscosity)
-52 viscoplasticity
$ <$ -100 user material routine with -kode-100 user defined constants with keyword *USER MATERIAL
PROCEDURE DESCRIPTION
iperturb(1) = 0 : linear
  = 1 : second order theory for frequency calculations following a static step (PERTURBATION selected)
  $ \ge$ 2 : Newton-Raphson iterative procedure is active
  = 3 : nonlinear material (linear or nonlinear geometric and/or heat transfer)
iperturb(2) 0 : linear geometric (NLGEOM not selected)
  1 : nonlinear geometric (NLGEOM selected)
nmethod 1 : static (linear or nonlinear)
  2 : frequency(linear)
  3 : buckling (linear)
  4 : dynamic (linear or nonlinear)
  5 : steady state dynamics
GEOMETRY DESCRIPTION
nk highest node number
co(i,j) coordinate i of node j
inotr(1,j) transformation number applicable in node j
inotr(2,j) a SPC in a node j in which a transformation applies corresponds to a MPC. inotr(2,j) contains the number of a new node generated for the inhomogeneous part of the MPC
TOPOLOGY DESCRIPTION
ne highest element number
mi(1) max # of integration points per element (max over all elements)
mi(2) max degree of freedom per node (max over all nodes) in fields like v(0:mi(2))...
  if 0: only temperature DOF
  if 3: temperature + displacements
  if 4: temperature + displacements/velocities + pressure
kon(i) field containing the connectivity lists of the elements in successive order
  for 1d and 2d elements (no composites) the 3d-expansion is stored first, followed by the topology of the original 1d or 2d element, for a shell composite this is followed by the topology of the expansion of each layer
For element i  
ipkon(i) (location in kon of the first node in the element connectivity list of element i)-1
lakon(i) element label
  C3D4: linear tetrahedral element (F3D4 for 3D-fluids)
  C3D6: linear wedge element (F3D6 for 3D-fluids)
  C3D6 E: expanded plane strain 3-node element = CPE3
  C3D6 S: expanded plane stress 3-node element = CPS3
  C3D6 A: expanded axisymmetric 3-node element = CAX3
  C3D6 L: expanded 3-node shell element = S3
  C3D8: linear hexahedral element (F3D8 for 3D-fluids)
  C3D8I: linear hexahedral element with incompatible modes
  C3D8I E: expanded plane strain 4-node element = CPE4
  C3D8I S: expanded plane stress 4-node element = CPS4
  C3D8I A: expanded axisymmetric 4-node element = CAX4
  C3D8I L: expanded 4-node shell element = S4
  C3D8I B: expanded 2-node beam element = B31
  C3D8R: linear hexahedral element with reduced integration (F3D8R for 3D-fluids)
  C3D8R E: expanded plane strain 4-node element with reduced integration = CPE4R
  C3D8R S: expanded plane stress 4-node element with reduced integration = CPS4R
  C3D8R A: expanded axisymmetric 4-node element with reduced integration = CAX4R
  C3D8R L: expanded 4-node shell element with reduced integration = S4R
  C3D8R B: expanded 2-node beam element with reduced integration = B31R
  C3D10: quadratic tetrahedral element (F3D10 for 3D-fluids)
  C3D15: quadratic wedge element (F3D15 for 3D-fluids)
  C3D15 E: expanded plane strain 6-node element = CPE6
  C3D15 S: expanded plane stress 6-node element = CPS6
  C3D15 A: expanded axisymmetric 6-node element = CAX6
  C3D15 L: expanded 6-node shell element = S6
  C3D20: quadratic hexahedral element (F3D20 for 3D-fluids)
  C3D20 E: expanded plane strain 8-node element = CPE8
  C3D20 S: expanded plane stress 8-node element = CPS8
  C3D20 A: expanded axisymmetric 8-node element = CAX8
  C3D20 L: expanded 8-node shell element = S8
  C3D20 B: expanded 3-node beam element = B32
  C3D20R: quadratic hexahedral element with reduced integration (F3D20R for 3D-fluids)
  C3D20RI: incompressible quadratic hexahedral element with reduced integration
  C3D20RE: expanded plane strain 8-node element with reduced integration = CPE8R
  C3D20RS: expanded plane stress 8-node element with reduced integration = CPS8R
  C3D20RA: expanded axisymmetric 8-node element with reduced integration = CAX8R
  C3D20RL: expanded 8-node shell element with reduced integration = S8R
  C3D20RLC: expanded composite 8-node shell element with reduced integration = S8R
  C3D20RB: expanded 3-node beam element with reduced integration = B32R
  GAPUNI: 2-node gap element
  ESPRNGA2 : 2-node spring element
  EDSHPTA2 : 2-node dashpot element
  ESPRNGC4 : 4-node contact spring element
  ESPRNGC5 : 5-node contact spring element
  ESPRNGC7 : 7-node contact spring element
  ESPRNGC9 : 9-node contact spring element
  network elements (D-type):]
  DATR : absolute to relative
  DCARBS : carbon seal
  DCARBSGE : carbon seal GE (proprietary)
  DCHAR : characteristic
  DGAPFA : gas pipe Fanno adiabatic
  DGAPFAA : gas pipe Fanno adiabatic Albers (proprietary)
  DGAPFAF : gas pipe Fanno adiabatic Friedel (proprietary)
  DGAPFI : gas pipe Fanno isothermal
  DGAPFIA : gas pipe Fanno isothermal Albers (proprietary)
  DGAPFIF : gas pipe Fanno isothermal Friedel (proprietary)
  DGAPIA : gas pipe adiabatic
  DGAPIAA : gas pipe adiabatic Albers (proprietary)
  DGAPIAF : gas pipe adiabatic Friedel (proprietary)
  DGAPII : gas pipe isothermal
  DGAPIIA : gas pipe isothermal Albers (proprietary)
  DGAPIIF : gas pipe isothermal Friedel (proprietary)
  DLABD : labyrinth dummy (proprietary)
  DLABFSN : labyrinth flexible single
  DLABFSP : labyrinth flexible stepped
  DLABFSR : labyrinth flexible straight
  DLABSN : labyrinth single
  DLABSP : labyrinth stepped
  DLABSR : labyrinth straight
  DLDOP : oil pump (proprietary)
  DLICH : channel straight
  DLICHCO : channel contraction
  DLICHDO : channel discontinuous opening
  DLICHDR : channel drop
  DLICHDS : channel discontinuous slope
  DLICHEL : channel enlargement
  DLICHRE : channel reservoir
  DLICHSG : channel sluice gate
  DLICHSO : channel sluice opening
  DLICHST : channel step
  DLICHWE : channel weir crest
  DLICHWO : channel weir slope
  DLIPIBE : (liquid) pipe bend
  DLIPIBR : (liquid) pipe branch (not available yet)
  DLIPICO : (liquid) pipe contraction
  DLIPIDI : (liquid) pipe diaphragm
  DLIPIEL : (liquid) pipe enlargement
  DLIPIEN : (liquid) pipe entrance
  DLIPIGV : (liquid) pipe gate valve
  DLIPIMA : (liquid) pipe Manning
  DLIPIMAF : (liquid) pipe Manning flexible
  DLIPIWC : (liquid) pipe White-Colebrook
  DLIPIWCF : (liquid) pipe White-Colebrook flexible
  DLIPU : liquid pump
  DLPBEIDC : (liquid) restrictor bend Idelchik circular
  DLPBEIDR : (liquid) restrictor bend Idelchik rectangular
  DLPBEMA : (liquid) restrictor own (proprietary)
  DLPBEMI : (liquid) restrictor bend Miller
  DLPBRJG : branch joint GE
  DLPBRJI1 : branch joint Idelchik1
  DLPBRJI2 : branch joint Idelchik2
  DLPBRSG : branch split GE
  DLPBRSI1 : branch split Idelchik1
  DLPBRSI2 : branch split Idelchik2
  DLPC1 : (liquid) orifice Cd=1
  DLPCO : (liquid) restrictor contraction
  DLPEL : (liquid) restrictor enlargement
  DLPEN : (liquid) restrictor entry
  DLPEX : (liquid) restrictor exit
  DLPLOID : (liquid) restrictor long orifice Idelchik
  DLPLOLI : (liquid) restrictor long orifice Lichtarowicz
  DLPUS : (liquid) restrictor user
  DLPVF : (liquid) vortex free
  DLPVS : (liquid) vortex forced
  DLPWAOR : (liquid) restrictor wall orifice
  DMRGF : Moehring centrifugal
  DMRGP : Moehring centripetal
  DORBG : orifice Bragg (proprietary)
  DORBT : bleed tapping
  DORC1 : orifice Cd=1
  DORMA : orifice proprietary, rotational correction Albers (proprietary)
  DORMM : orifice McGreehan Schotsch, rotational correction McGreehan and Schotsch
  DORPA : orifice Parker and Kercher, rotational correction Albers (proprietary)
  DORPM : orifice Parker and Kercher, rotational correction McGreehan and Schotsch
  DORPN : preswirl nozzle
  DREBEIDC : restrictor bend Idelchik circular
  DREBEIDR : restrictor bend Idelchik rectangular
  DREBEMA : restrictor own (proprietary)
  DREBEMI : restrictor bend Miller
  DREBRJG : branch joint GE
  DREBRJI1 : branch joint Idelchik1
  DREBRJI2 : branch joint Idelchik2
  DREBRSG : branch split GE
  DREBRSI1 : branch split Idelchik1
  DREBRSI2 : branch split Idelchik2
  DRECO : restrictor contraction
  DREEL : restrictor enlargement
  DREEN : restrictor entrance
  DREEX : restrictor exit
  DRELOID : restrictor long orifice Idelchik
  DRELOLI : restrictor long orifice Lichtarowicz
  DREUS : restrictor user
  DREWAOR : restrictor wall orifice
  DRIMS : rim seal (proprietary)
  DRTA : relative to absolute
  DSPUMP : scavenge pump (proprietary)
  DVOFO : vortex forced
  DVOFR : vortex free
ielorien(j,i) orientation number of layer j
ielmat(j,i) material number of layer j
ielprop(i) property number (for gas networks)
SETS AND SURFACES
nset number of sets (including surfaces)
ialset(i) member of a set or surface: this is a
  - node for a node set or nodal surface
  - element for an element set
  - number made up of 10*(element number)+facial number for an element face surface
  if ialset(i)=-1 it means that all nodes or elements (depending on the kind of set) in between ialset(i-2) and ialset(i-1) are also member of the set
For set i  
set(i) name of the set; this is the user defined name
  + N for node sets
  + E for element sets
  + S for nodal surfaces
  + T for element face surfaces
istartset(i) pointer into ialset containing the first set member
iendset(i) pointer into ialset containing the last set member
TIE CONSTRAINTS
ntie number of tie constraints
For tie constraint i  
tieset(1,i) name of the tie constraint;
  for contact constraints (which do not have a name) the adjust nodal set name is stored, if any, and a C is appended at the end
  for multistage constraints a M is appended at the end
  for a contact tie a T is appended at the end
  for submodels (which do not have a name) a fictitious name SUBMODELi is used, where i is a three-digit consecutive number and a S is appended at the end
tieset(2,i) dependent surface name + S
tieset(3,i) independent surface name
  + S for nodal surfaces
  + T for element face surfaces
tietol(1,i) tie tolerance; used for cyclic symmetry ties
  special meaning for contact pairs:
  $ >$ 0 for large sliding
  $ <$ 0 for small sliding
  if $ \vert$tietol$ \vert$ $ \ge$ 2, adjust value = $ \vert$tietol$ \vert$-2
tietol(2,i) only for contact pairs: number of the relevant interaction definition (is treated as a material)
CONTACT
ncont total number of triangles in the triangulation of all independent surfaces
ncone total number of slave nodes in the contact formulation
For triangle i  
koncont(1..3,i) nodes belonging to the triangle
koncont(4,i) element face to which the triangle belongs: 10*(element number) + face number
cg(1..3,i) global coordinates of the center of gravity
straight(1..4,i) coefficients of the equation of the plane penpendicular to the triangle and containing its first edge (going through the first and second node of koncont)
straight(5..8,i) idem for the second edge
straight(9..12,i) idem for the third edge
straight(13..16,i) coefficients of the equation of the plane containing the triangle
For contact tie constraint i  
itietri(1,i) first triangle in field koncont of the master surface corresponding to contact tie constraint i
itietri(2,i) last triangle in field koncont of the master surface corresponding to contact tie constraint i
SHELL (2D) AND BEAM (1D) VARIABLES (INCLUDING PLANE STRAIN, PLANE STRESS AND AXISYMMETRIC ELEMENTS)
iponor(2,i) two pointers for entry i of kon. The first pointer points to the location in xnor preceding the normals of entry i, the second points to the location in knor of the newly generated dependent nodes of entry i.
xnor(i) field containing the normals in nodes on the elements they belong to
knor(i) field containing the extra nodes needed to expand the shell and beam elements to volume elements
thickn(2,i) thicknesses (one for shells, two for beams) in node i
thicke(j,i) thicknesses (one (j=1) for non-composite shells, two (j=1,2) for beams and n (j=1..n) for composite shells consisting of n layers) in element nodes. The entries correspond to the nodal entries in field kon
offset(2,i) offsets (one for shells, two for beams) in element i
iponoel(i) pointer for node i into field inoel, which stores the 1D and 2D elements belonging to the node.
inoel(3,i) field containing an element number, a local node number within this element and a pointer to another entry (or zero if there is no other).
inoelfree next free field in inoel
rig(i) integer field indicating whether node i is a rigid node (nonzero value) or not (zero value). In a rigid node or knot all expansion nodes except the ones not in the midface of plane stress, plane strain and axisymmetric elements are connected with a rigid body MPC. If node i is a rigid node rig(i) is the number of the rotational node of the knot; if the node belongs to axisymmetric, plane stress and plane strain elements only, no rotational node is linked to the knot and rig(i)=-1
AMPLITUDES
nam # amplitude definitions
amta(1,j) time of (time,amplitude) pair j
amta(2,j) amplitude of (time,amplitude) pair j
namtot total # of (time,amplitude) pairs
For amplitude i  
amname(i) name of the amplitude
namta(1,i) location of first (time,amplitude) pair in field amta
namta(2,i) location of last (time,amplitude) pair in field amta
namta(3,i) in absolute value the amplitude it refers to; if abs(namta(3,i))=i it refers to itself. If abs(namta(3,i))=j, amplitude i is a time delay of amplitude j the value of which is stored in amta(1,namta(1,i)); in the latter case amta(2,namta(1,i)) is without meaning; If namta(3,i)$ >$0 the time in amta for amplitude i is step time, else it is total time.
TRANSFORMS
ntrans # transform definitions
trab(1..6,i) coordinates of two points defining the transform
trab(7,i) =-1 for cylindrical transformations
  =1 for rectangular transformations
SINGLE POINT CONSTRAINTS
nboun # SPC's
For SPC i  
nodeboun(i) SPC node
ndirboun(i) SPC direction
typeboun(i) SPC type (SPCs can contain the nonhomogeneous part of MPCs)
  B=prescribed boundary condition
  M=midplane
  P=planempc
  R=rigidbody
  S=straightmpc
  U=usermpc
  L=submodel
xboun(i) magnitude of constraint at end of a step
xbounold(i) magnitude of constraint at beginning of a step
xbounact(i) magnitude of constraint at the end of the present increment
xbounini(i) magnitude of constraint at the start of the present increment
iamboun(i) amplitude number
  for submodels the step number is inserted
ikboun(i) ordered array of the DOFs corresponding to the SPC's (DOF=8*(nodeboun(i)-1)+ndirboun(i))
ilboun(i) original SPC number for ikboun(i)
MULTIPLE POINT CONSTRAINTS
j=ipompc(i) starting location in nodempc and coefmpc of MPC i
nodempc(1,j) node of first term of MPC i
nodempc(2,j) direction of first term of MPC i
k=nodempc(3,j) next entry in field nodempc for MPC i (if zero: no more terms in MPC)
coefmpc(j) first coefficient belonging to MPC i
nodempc(1,k) node of second term of MPC i
nodempc(2,k) direction of second term of MPC i
coefmpc(k) coefficient of second term of MPC i
ikmpc (i) ordered array of the dependent DOFs corresponding to the MPC's DOF=8*(nodempc(1,ipompc(i))-1)+nodempc(2,ipompc(i))
ilmpc (i) original MPC number for ikmpc(i)
icascade 0 : MPC's did not change since the last iteration
  1 : MPC's changed since last iteration : dependency check in cascade.c necessary
  2 : at least one nonlinear MPC had DOFs in common with a linear MPC or another nonlinear MPC. dependency check is necessary in each iteration
POINT LOADS
nforc # of point loads
For point load i  
nodeforc(1,i) node in which force is applied
nodeforc(2,i) sector number, if force is real; sector number + # sectors if force is imaginary (only for modal dynamics and steady state dynamics analyses with cyclic symmetry)
ndirforc(i) direction of force
xforc(i) magnitude of force at end of a step
xforcold(i) magnitude of force at start of a step
xforcact(i) actual magnitude
iamforc(i) amplitude number
ikforc(i) ordered array of the DOFs corresponding to the point loads (DOF=8*(nodeboun(i)-1)+ndirboun(i))
ilforc(i) original SPC number for ikforc(i)
FACIAL DISTRIBUTED LOADS
nload # of facial distributed loads
For distributed load i  
nelemload(1,i) element to which distributed load is applied
nelemload(2,i) node for the environment temperature (only for heat transfer analyses); sector number, if load is real; sector number + # sectors if load is imaginary (only for modal dynamics and steady state dynamics analyses with cyclic symmetry)
sideload(i) load label; indicated element side to which load is applied
xload(1,i) magnitude of load at end of a step or, for heat transfer analyses, the convection (*FILM) or the radiation coefficient (*RADIATE)
xload(2,i) the environment temperature (only for heat transfer analyses
xloadold(1..2,i) magnitude of load at start of a step
xloadact(1..2,i) actual magnitude of load
iamload(1,i) amplitude number for xload(1,i)
  for submodels the step number is inserted
iamload(2,i) amplitude number for xload(2,i)
MASS FLOW RATE
nflow # of network elements
TEMPERATURE LOADS
t0(i) initial temperature in node i at the start of the calculation
t1(i) temperature at the end of a step in node i
t1old(i) temperature at the start of a step in node i
t1act(i) actual temperature in node i
iamt1(i) amplitude number
MECHANICAL BODY LOADS
nbody # of mechanical body loads
For body load i  
ibody(1,i) code identifying the kind of body load
  1: centrifugal loading
  2: gravity loading with known gravity vector
  3: generalized gravity loading
ibody(2,i) amplitude number for load i
ibody(3,i) load case number for load i
cbody(i) element number or element set to which load i applies
xbody(1,i) size of the body load
xbody(2..4,i) for centrifugal loading: point on the axis
  for gravity loading with known gravity vector: normalized gravity vector
xbody(5..7,i) for centrifugal loading: normalized vector on the rotation axis
xbodyact(1,i) actual magnitude of load
xbodyact(2..7,i) identical to the corresponding entries in xbody
For element i  
ipobody(1,i) body load applied to element i, if any, else 0
ipobody(2,i) index referring to the line in field ipobody containing the next body load applied to element i, i.e. ipobody(1,ipobody(2,i)), else 0
STRESS, STRAIN AND ENERGY FIELDS
eei(i,j,k) in general : Lagrange strain component i in integration point j of element k (linear strain in linear elastic calculations)
  for elements with &sstarf#star;DEFORMATION PLASTICITY property: Eulerian strain component i in integration point j of element k (linear strain in linear elastic calculations)
eeiini(i,j,k) Lagrange strain component i in integration point of element k at the start of an increment
een(i,j) Lagrange strain component i in node j (mean over all adjacent elements linear strain in linear elastic calculations)
stx(i,j,k) Cauchy or PK2 stress component i in integration point j of element k at the end of an iteration (linear stress in linear elastic calculations).
  For spring elements stx(1..3,1,k) contains the relative displacements for element k and stx(4..6,1,k) the contact stresses
sti(i,j,k) PK2 stress component i in integration point j of element k at the start of an iteration (linear stress in linear elastic calculations)
stiini(i,j,k) PK2 stress component i in integration point j of element k at the start of an increment
stn(i,j) Cauchy stress component i in node j (mean over all adjacent elements; "linear" stress in linear elastic calculations)
ener(j,k) strain energy in integration point j of element k
ener(j,ne+k) kinetic energy in integration point j of element k (only for *EL PRINT)
enerini(j,k) strain energy in integration point of element k at the start of an increment
enern(j) strain energy in node j (mean over all adjacent elements
THERMAL ANALYSIS
ithermal(1) 0 : no temperatures involved in the calculation
(in this manual also 1 : stress analysis with given temperature field
called ithermal) 2 : thermal analysis (no displacements)
  3 : coupled thermal-mechanical analysis : temperatures and displacements are solved for simultaneously
ithermal(2) used to determine boundary conditions for plane stress, plane strain and axisymmetric elements
  0 : no temperatures involved in the calculation
  1 : no heat transfer nor coupled steps in the input deck
  2 : no mechanical nor coupled steps in the input deck
  3 : at least one mechanical and one thermal step or at least one coupled step in the input deck
v(0,j) temperature of node j at the end of an iteration (for ithermal $ >$ 1)
vold(0,j) temperature of node j at the start of an iteration (for ithermal $ >$ 1)
vini(0,j) temperature of node j at the start of an increment (for ithermal $ >$ 1)
fn(0,j) actual temperature at node j (for ithermal $ >$ 1)
qfx(i,j,k) heat flux component i in integration point j of element k at the end of an iteration
qfn(i,j) heat flux component i in node j (mean over all adjacent elements)
DISPLACEMENTS AND SPATIAL/TIME DERIVATIVES
v(i,j) displacement of node j in direction i at the end of an iteration
vold(i,j) displacement of node j in direction i at the start of an iteration
vini(i,j) displacement of node j in direction i at the start of an increment
ve(i,j) velocity of node j in direction i at the end of an iteration
veold(i,j) velocity of node j in direction i at the start of an iteration
veini(i,j) velocity of node j in direction i at the start of an increment
accold(i,j) acceleration of node j in direction i at the start of an iteration
accini(i,j) acceleration of node j in direction i at the start of an increment
vkl(i,j) (i,j) component of the displacement gradient tensor at the end of an iteration
xkl(i,j) (i,j) component of the deformation gradient tensor at the end of an iteration
xikl(i,j) (i,j) component of the deformation gradient tensor at the start of an increment
ckl(i,j) (i,j) component of the inverse of the deformation gradient tensor
LINEAR EQUATION SYSTEM
ad(i) element i on diagonal of stiffness matrix
au(i) element i in upper triangle of stiffness matrix
adb(i) element i on diagonal of mass matrix, or, for buckling, of the incremental stiffness matrix (only nonzero elements are stored)
aub(i) element i in upper triangle of mass matrix, or, for buckling, of the incremental stiffness matrix (only nonzero elements are stored)
neq[0] # of mechanical equations
neq[1] sum of mechanical and thermal equations
neq[2] neq[1] + # of single point constraints (only for modal calculations)
nzl number of the column such that all columns with a higher column number do not contain any (projected) nonzero off-diagonal terms ($ \le$ neq[1])
nzs[0] sum of projected nonzero mechanical off-diagonal terms
nzs[1] nzs[0]+sum of projected nonzero thermal off-diagonal terms
nzs[2] nzs[1] + sum of nonzero coefficients of SPC degrees of freedom (only for modal calculations)
nactdof(i,j) actual degree of freedom (in the system of equations) of DOF i of node j (0 if not active)
INTERNAL AND EXTERNAL FORCES
fext(i) external mechanical forces in DOF i (due to point loads and distributed loads, including centrifugal and gravity loads, but excluding temperature loading and displacement loading)
fextini(i) external mechanical forces in DOF i (due to point loads and distributed loads, including centrifugal and gravity loads, but excluding temperature loading and displacement loading) at the end of the last increment
finc(i) external mechanical forces in DOF i augmented by contributions due to temperature loading and prescribed displacements; used in linear calculations only
f(i) actual internal forces in DOF i due to :
  actual displacements in the independent nodes;
  prescribed displacements at the end of the increment in the dependent nodes;
  temperatures at the end of the increment in all nodes
fini(i) internal forces in DOF i at the end of the last increment
b(i) right hand side of the equation system : difference between fext and f in nonlinear calcultions; for linear calculations, b=finc.
fn(i,j) actual force at node j in direction i
INCREMENT PARAMETERS
tinc user given increment size (can be modified by the program if the parameter DIRECT is not activated)
tper user given step size
dtheta normalized (by tper) increment size
theta normalized (by tper) size of all previous increments (not including the present increment)
reltime theta+dtheta
dtime real time increment size
time real time size of all previous increments INCLUDING the present increment
ttime real time size of all previous steps and increments EXCLUDING the present increment
DIRECT INTEGRATION DYNAMICS
alpha,bet,gam parameter in the alpha-method of Hilber, Hughes and Taylor
iexpl =0 : implicit dynamics
  =1 : explicit dynamics
FREQUENCY CALCULATIONS
mei[0] number of requested eigenvalues
mei[1] number of Lanczos vectors
mei[2] maximum number of iterations
mei[3] if 1: store eigenfrequencies, eigenmodes, mass matrix and possibly stiffness matrix in .eig file, else 0
fei[0] tolerance (accuracy)
fei[1] lower value of requested frequency range
fei[2] upper value of requested frequency range
CYCLIC SYMMETRY CALCULATIONS
mcs number of cyclic symmetry parts
ics one-dimensional field; contains all independent nodes, one part after the other, and sorted within each part
rcs one-dimensional field; contains the corresponding radial coordinates
zcs one-dimensional field; contains the corresponding axial coordinates
For cyclic symmetry part i  
cs(1,i) number of segments in $ 360^\circ$
cs(2,i) minimum nodal diameter
cs(3,i) maximum nodal diameter
cs(4,i) number of nodes on the independent side
cs(5,i) number of sections to be plotted
cs(6..12,i) coordinates of two points on the cyclic symmetry axis
cs(13,i) number of the element set (for plotting purposes)
cs(14,i) total number of independent nodes in all previously defined cyclic symmetry parts
cs(15,i) cos(angle) where angle = 2*$ \pi$/cs(1,mcs)
cs(16,i) sin(angle) where angle = 2*$ \pi$/cs(1,mcs)
cs(17,i) number of tie constraint
MODAL DYNAMICS AND STEADY STATE DYNAMICS CALCULATIONS
  For Rayleigh damping (modal and steady state dynamics)
xmodal(1) $ \alpha_m$ (first Rayleigh coefficient)
xmodal(2) $ \beta_m$ (second Rayleigh coefficient)
  For steady state dynamics
xmodal(3) lower frequency bound $ f_{min}$
xmodal(4) upper frequency bound $ f_{max}$
xmodal(5) number of data points $ n_{data} +0.5$
xmodal(6) bias
xmodal(7) if harmonic: -0.5; if not harmonic: number of Fourier coefficients + 0.5
xmodal(8) lower time bound $ t_{min}$ for one period (nonharmonic loading)
xmodal(9) upper time bound $ t_{max}$ for one period (nonharmonic loading)
  For damping (modal and steady state dynamics)
xmodal(10) internal number of node set for which results are to be calculated
xmodal(11) for Rayleigh damping: -0.5
  for direct damping: largest mode for which $ \zeta$ is defined +0.5
  For direct damping
xmodal(12.. values of the $ \zeta$ coefficients
int(xmodal(11)))  
OUTPUT IN .DAT FILE
prset(i) node or element set corresponding to output request i
prlab(i) label corresponding to output request i. It contains 6 characters. The first 4 are reserved for the field name, e.g. 'U ' for displacements, the fifth for the value of the TOTALS parameter ('T' for TOTALS=YES, 'O' for TOTALS=ONLY and ' ' else) and the sixth for the value of the GLOBAL parameter ('G' for GLOBAL=YES and 'L' for GLOBAL=NO).
nprint number of print requests
OUTPUT IN .FRD FILE
filab(i) label corresponding to output field i. It contains 6 characters. The first 4 are reserved for the field name. The order is fixed: filab(1)='U ', filab(2)='NT ',filab(3)='S ',filab(4)='E ', filab(5)='RF ', filab(6)='PEEQ', filab(7)='ENER', filab(8)='SDV ', filab(9)='HFL ', filab(10)='RFL ', filab(11)='PU ', filab(12)='PNT ', filab(13)='ZZS ', filab(14)='TT ', filab(15)='MF ', filab(16)='PT ', filab(17)='TS ', filab(18)='PHS ', filab(19)='MAXU',filab(20)='MAXS', filab(21)='V ',filab(22)='PS ',filab(23)='MACH', filab(24)='CP ', filab(25)='TURB', filab(26)='CONT ' filab(27)='CELS ', filab(28)='DEPT ', filab(29)='HCRI ', filab(30)='MAXE', filab(31)='PRF ' and filab(32)='ME '. Results are stored for the complete mesh. A field is not selected if the first 4 characters are blank, e.g. the stress is not stored if filab(3)(1:4)=' '. An exception to this rule is formed for filab(1): here, only the first three characters are used and should be either 'U ' or ' ', depending on whether displacements are requested are not. The fourth character takes the value 'I' if the user wishes that the displacements of the iterations of the last increment are stored (used for debugging in case of divergence), else it is blank. If the mesh contains 1D or 2D elements, the fifth character takes the value 'I' if the results are to be interpolated, 'M' if the section forces are requested instead of the stresses and 'E' if the 1D/2D element results are to be given on the expanded elements. In all other cases the fifth character is blank: ' '. The sixth character contains the value of the GLOBAL parameter ('G' for GLOBAL=YES and 'L' for GLOBAL=NO). The entries filab(13)='RFRES ' and filab(14)='RFLRES' are reserved for the output of the residual forces and heat fluxes in case of no convergence and cannot be selected by the user: the residual forces and heat fluxes are automatically stored if the calculation stops due to divergence.
inum(i) =-1: network node
  =1: structural node or 3D fluid node
CONVECTION NETWORKS
ntg number of gas nodes
For gas node i  
itg(i) global node number
nactdog(j,i) if $ \ne$ 0 indicates that degree of freedom j of gas node i is is an unknown; the nonzero number is the column number of the DOF in the convection system of equations. The physical significance of j depends on whether the node is a midside node or corner node of a fluid element:
  j=0 and corner node: total temperature
  j=1 and midside node: mass flow
  j=2 and corner node: total pressure
  j=3 and midside node: geometry (e.g. $ \alpha$ for a gate valve)
nacteq(j,i) if $ \ne$ 0 indicates that equation type j is active in gas node i; the nonzero number is the row number of the DOF in the convection system of equations. The equation type of j depends on whether the node is a midside node or corner node of a network element:
  j=0 and corner node: conservation of energy
  j=1 and corner node: conservation of mass
  j=2 and midside node: convervation of momentum
ineighe(i) only for gas network nodes (no liquids):
  if 0: itg(i) is a midside node
  if -1: itg(i) is a chamber
  if $ >$ 0: ineighe(i) is a gas pipe element itg(i) belongs to
   
v(j,i) value of degree of freedom j in node i (global numbering). The physical significance of j depends on whether the node is a midside node or corner node of a network element:
  j=0 and corner node: total temperature
  j=1 and midside node: mass flow
  j=2 and corner node: total pressure
  j=3 and corner node: static temperature
  j=3 and midside node: geometry
   
nflow number of network elements
ieg(i) global element number corresponding to network element i
network if 0: purely thermal (only unknowns: total temperature)
  if 1: coupled thermodynamic network
  if 2: purely aerodynamic (total temperature is known everywhere)
THERMAL RADIATION
ntr number of element faces loaded by radiation = radiation faces
iviewfile $ < 0$: reading the viewfactors from file
  $ \ge 0$: calculating the viewfactors
   
$ \vert$ iviewfile $ \vert$ $ \ge 2$: write the viewfactors to file
  $ < 2$: do not write the viewfactors to file
  $ = 3$: stop after storing the viewfactors to file
For radiation face i  
kontri(1..3,j) nodes belonging to triangle j
kontri(4,j) radiation face number ($ > 0$ and $ \le$ ntri)to which triangle j belongs
nloadtr(i) distributed load number ($ > 0$ and $ \le$ nload) corresponding to radiation face i
ITERATION VARIABLES
istep step number
iinc increment number
iit iteration number
  = -1 only before the first iteration in the first increment of a step
  = 0 before the first iteration in an increment which was repeated due to non-convergence or any other but the first increment of a step
  $ > 0$ denotes the actual iteration number
PHYSICAL CONSTANTS
physcon(1) Absolute zero
physcon(2) Stefan-Boltzmann constant
physcon(3) Newton Gravity constant
physcon(4) Static temperature at infinity (for 3D fluids)
physcon(5) Velocity at infinity (for 3D fluids)
physcon(6) Static pressure at infinity (for 3D fluids)
physcon(7) Density at infinity (for 3D fluids)
physcon(8) Typical size of the computational domain (for 3D fluids)
physcon(9) Perturbation parameter
  if $ 0 \le physcon(9) < 1$: laminar
  if $ 1 \le physcon(9) < 2$: k-$ \epsilon$ Model
  if $ 2 \le physcon(9) < 3$: q-$ \omega$ Model
  if $ 3 \le physcon(9) < 4$: SST Model
COMPUTATIONAL FLUID DYNAMICS
vold(0,i) Static temperature in node i
vold(1..3,i) Velocity components in node i
vold(4,i) Pressure in node i
voldaux(0,i) Total energy density $ \rho \epsilon_t$ in node i
voldaux(1..3,i) Momentum density components $ \rho v_i$ in node i
voldaux(4,i) Density $ \rho$ in node i
v(0,i) Total energy density correction in node i
v(1..3,i) Momentum density correction components in node i
v(4,i) For fluids: Pressure correction in node i
  For gas: Density correction in node i
CONVERGENCE PARAMETERS
qam[0] $ \tilde{q}^{\alpha}_i$ for the mechanical forces
qam[1] $ \tilde{q}^{\alpha}_i$ for the concentrated heat flux
ram[0] $ r^{\alpha}_{i,max}$ for the mechanical forces
ram[1] $ r^{\alpha}_{i,max}$ for the concentrated heat flux
ram[2] the node corresponding to ram[0]
ram[3] the node corresponding to ram[1]
uam[0] $ {\Delta u}^{\alpha}_{i,max}$ for the displacements
uam[1] $ {\Delta u}^{\alpha}_{i,max}$ for the temperatures
cam[0] $ {c}^{\alpha}_{i,max}$ for the displacements
cam[1] $ {c}^{\alpha}_{i,max}$ for the temperatures
cam[2] largest temperature change within the increment
cam[3] node corresponding to cam[0]
cam[4] node corresponding to cam[1]
  for networks
uamt largest increment of gas temperature
camt[0] largest correction to gas temperature
camt[1] node corresponding to camt[0]
uamf largest increment of gas massflow
camf[0] largest correction to gas massflow
camf[1] node corresponding to camt[0]
uamp largest increment of gas pressure
camp[0] largest correction to gas pressure
camp[1] node corresponding to camt[0]
THREE-DIMENSIONAL INTERPOLATION
cotet(1..3,i) coordinates of nodes i
kontet(1..4,i) nodes belonging to tetrahedron i
ipofa(i) entry in field inodfa pointing to a face for which node i is the smallest number
inodfa(1..3,i) nodes j, k and l belonging to face i such that $ j<k<l$
inodfa(4,i) number of another face for which inodfa(1,i) is the smallest number. If no other exists the value is zero
planfa(1..4,i) coefficients a, b, c and d of the plane equation ax+by+cz+d=0 of face i
ifatet(1..4,i) faces belonging to tetrahedron i. The sign identifies the half space to which i belongs if evaluating the plane equation of the face

It is important to notice the difference between cam[1] and cam[2]. cam[1] is the largest change within an iteration of the actual increment. If the corrections in subsequent iterations all belonging to the same increment are 5,1,0.1, the value of cam[1] is 5. cam[2] is the largest temperature change within the increment, in the above example this is 6.1.


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guido dhondt 2012-10-06