Read/Write Format
-------------------------------------- ------------------
AIRFOIL_NAME ML,NL,MD,ND,MM,NM A30,6I2,6I2
M(1) ... ... M(ML) 7X,9F7.0
AL(1) CL(1,1) ... ... CL(1,NL) 10F7.0/(7X,9F7.0)
. . . .
. . . .
. . . .
AL(NL) CL(NL,1) ... ... CL(NL,ML) 10F7.0/(7X,9F7.0)
M(1) ... ... M(MD) 7X,9F7.0
AD(1) CD(1,1) ... ... CD(1,ND) 10F7.0/(7X,9F7.0)
. . . .
. . . .
. . . .
AD(ND) CD(ND,1) ... ... CD(ND,MD) 10F7.0/(7X,9F7.0)
M(1) ... ... M(MM) 7X,9F7.0
AM(1) CM(1,1) ... ... CM(1,NM) 10F7.0/(7X,9F7.0)
. . . .
. . . .
. . . .
AM(NM) CM(NM,1) ... ... CM(NM,MM) 10F7.0/(7X,9F7.0)
AL = Lift coefficient angles of attack
AD = Drag coefficient angles of attack
AM = Pitching moment coefficient angles of attack
ML = Number of lift coefficient Machs
NL = Number of lift coefficient alphas
MD = Number of drag coefficient Machs
