*HEADING
: NAFEMS TEST 2, wrapped thick cylinder [S8R]
*NODE
10001, 
11,0.,23.
19,23.,0.
*NGEN,LINE=C,NSET=LHS
11,19,1,10001
*NCOPY,CHANGE NUMBER=800,OLD SET=LHS,SHIFT,NEW SET=RHS
0.,0.,-100.

*NFILL,NSET=NALL
LHS,RHS,8,100
*NSET,NSET=AB,GEN
19,819,100
*NSET,NSET=CD,GEN
11,811,100
*ELSET,ELSET=CD
11,211,411,611
*ELSET,ELSET=AB
17,217,417,617
*NORMAL
CD,CD,0.,1.,0.
AB,AB,1.,0.,0.
*ELEMENT,TYPE=S8R,ELSET=ELALL
11,11,13,213,211,12,113,212,111
*ELGEN,ELSET=ELALL
11,4,2,2,4,200,200
*ELSET,ELSET=OUTPUT
11, 
** The two innermost shell layers are made of material "none,"
** which has negligible stiffness.  These layers are added
** to the model so that the shell midplane lies at a radius of 23.
** We want the midplane to be at 23 because the pressure load is
** applied to the midplane, not to the surface of the shell.  
*SHELL SECTION,ELSET=ELALL,COMPOSITE
2.,3,NONE
2.,3,NONE
2.,3,INNER
2.,3,OUTER,ORIENT
*MATERIAL,NAME=NONE
*ELASTIC
1.E2,0.
*MATERIAL,NAME=INNER
*ELASTIC
2.1E5,.3
*EXPANSION
2.E-5, 
*MATERIAL,NAME=OUTER
*ELASTIC,TYPE=LAMINA
1.3E5,5.E3,.25,1.E4,1.E4,5.E3
*EXPANSION,TYPE=ORTHO
3.E-6,2.E-5,2.E-5
*ORIENTATION,NAME=ORIENT,SYSTEM=CYLINDRICAL,DEFINITION=COORDINATES
0.,0.,0.,0.,0.,-1.
1,0.
*BOUNDARY
LHS,3
AB,2
AB,6
CD,1
CD,6
**
*STEP
*STATIC
*DLOAD
ELALL,P,200.
*EL FILE,ELSET=OUTPUT,POSITION=NODES
7,8,9,10,11,12
S, 
*END STEP
*STEP
*STATIC
*TEMPERATURE
NALL,130.
*END STEP