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