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+
+C
+C---- Pointers for referencing polar force coefficients
+C First 4 pointers must be main polar plot variables.
+C
+ PARAMETER (
+ & IAL = 1, ! alpha
+ & ICL = 2, ! CL
+ & ICD = 3, ! CD
+ & ICM = 4, ! Cm
+ & ICW = 5, ! CDwave
+ & ICV = 6, ! CDvisc
+ & ICP = 7, ! CDpres
+ & IMA = 8, ! Mach
+ & IRE = 9, ! Re
+ & INC = 10, ! Ncrit
+ & ICH = 11, ! Hinge moment
+ & IMC = 12, ! Minimum Cp on surface
+ & ICDH = 13, ! CDh (engine thrust coeff.)
+ & ICMDOT = 14 ) ! Cm_dot
+ PARAMETER (IPTOT=14)
+C
+C
+C---------------------
+C Pointers for referencing polar airfoil-side quantities
+C
+ PARAMETER (
+ & JTP = 1, ! trip
+ & JTN = 2 ) ! transition
+ PARAMETER (JPTOT=2)
+
+ CHARACTER*10 CPOLNAME(IPTOT)
+ CHARACTER*5 CPOLSNAME(JPTOT)
+ CHARACTER*6 CPOLFORM(IPTOT), CPOLSFORM(JPTOT)
+C
+ DATA CPOLNAME /
+ & 'alpha ',
+ & 'CL ',
+ & 'CD ',
+ & 'CM ',
+ & 'CDw ',
+ & 'CDv ',
+ & 'CDp ',
+ & 'Mach ',
+ & 'Re ',
+ & 'Ncrit ',
+ & 'Chinge ',
+ & 'Cpmin ',
+ & 'CDh ',
+ & 'Cmdot ' /
+ DATA CPOLFORM /
+ & 'F7.3 ', ! alpha
+ & 'F9.4 ', ! CL
+ & 'F10.5 ', ! CD
+ & 'F9.4 ', ! CM
+ & 'F10.5 ', ! CDw
+ & 'F10.5 ', ! CDv
+ & 'F10.5 ', ! CDp
+ & 'F8.4 ', ! Mach
+ & 'E11.3 ', ! Re
+ & 'F7.3 ', ! Ncrit
+ & 'F10.5 ', ! Chinge
+ & 'F9.4 ', ! Cpmin
+ & 'F11.5 ', ! CDh
+ & 'F9.5 ' / ! Cmdot
+
+ DATA CPOLSNAME /
+ & 'Xtrip',
+ & 'Xtr ' /
+ DATA CPOLSFORM /
+ & 'F9.4 ', ! Xtrip
+ & 'F9.4 ' / ! Xtr