C DATA FILE
C
2, Number of Materials.
C
C** MATERIAL 1: GRAPHITE-EPOXY (T300/N5208) **
C
22.D+06, Young's Modulus - 1 Direction (E1 -psi)
1.5D+06, Young's Modulus - 2 Direction (E2 - psi)
0.25D+00, Poisson's Ratio (NU12)
0.52D+06, Shear Modulus (G12 - psi)
0.00525D+00, Thickness of Each Individual Ply (in.)
9.89D-03, Allowable Strain (Epsilon-1)
3.87D-03, Allowable Strain (Epsilon-2)
1.9D-02, Allowable Shear Strain (Gamma12)
0.0055D+00, Material Density (lb/in3)
3.D+00, Cost factor
C
C** MATERIAL 2: ARAMID-EPOXY (KEVLAR 49/CE3305) **
C
11.9D+06, Young's Modulus - 1 Direction (E1 -psi)
0.6D+06, Young's Modulus - 2 Direction (E2 - psi)
0.25D+00, Poisson's Ratio (NU12)
0.4D+06, Shear Modulus (G12 - psi)
0.00716D+00, Thickness of Each Individual Ply (in.)
2.87D-03, Allowable Strain (Epsilon-1)
3.00D-03, Allowable Strain (Epsilon-2)
1.21D-02, Allowable Shear Strain (Gamma12)
0.0048D+00, Material Density (lb/in3)
1.D+00, Cost factor
C
C
C
1, Obj. fnctn type (between 0 and 1) 
C              0=laminate cost; 1= laminate weight
C
2.0D+00, Unbalanced Laminate Penalty (set to 0 for unbal. laminates)
2.7D+00, Constraint Penalty Parameter. Increment by 0.1 
C    if GA is Generating Infeasible Laminates That Are Very Thin
C
C***********  Plate Properties & Loading Conditions ***********
C
-100.D+00, In-Plane Load - X Direction (negative is compression)
0.D+00, In-Plane Load - Y Direction (negative is compression)
0.D+00, In-Plane Shear Load
2, Modal shape - M (M <= 10)
2, Modal shape - N (N <= 10)
C
C*********** Other Code Inputs ************
C
C
100