From 0d4f43d355de79178b1142e9735902cf641670b6 Mon Sep 17 00:00:00 2001 From: Dimitri Sokolyuk Date: Mon, 11 May 2009 00:27:49 +0000 Subject: Xfoil 6.97 --- src/PINDEX.INC | 72 ++++++++++++++++++++++++++++++++++++++++++++++++++++++++++ 1 file changed, 72 insertions(+) create mode 100644 src/PINDEX.INC (limited to 'src/PINDEX.INC') diff --git a/src/PINDEX.INC b/src/PINDEX.INC new file mode 100644 index 0000000..1786198 --- /dev/null +++ b/src/PINDEX.INC @@ -0,0 +1,72 @@ + +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 -- cgit v1.2.3