GOE 117 (MVA MK.4) AIRFOIL (goe117-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 117 (MVA MK.4) AIRFOIL (goe117-il) Reynolds number: 100,000 Max Cl/Cd: 58.38 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe117-il-100000.txt Download as CSV file: xf-goe117-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 117 (MVA MK.4) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.2539 0.09320 0.08885 -0.0380 1.0000 0.1012
-8.500 -0.2638 0.09140 0.08715 -0.0376 1.0000 0.1047
-8.250 -0.2859 0.09090 0.08678 -0.0368 1.0000 0.1060
-8.000 -0.3107 0.09072 0.08674 -0.0349 1.0000 0.1064
-7.750 -0.2899 0.08522 0.08123 -0.0318 1.0000 0.1098
-7.500 -0.2952 0.08349 0.07956 -0.0291 1.0000 0.1129
-7.250 -0.3091 0.08231 0.07847 -0.0266 1.0000 0.1154
-7.000 -0.3295 0.08163 0.07790 -0.0241 1.0000 0.1172
-6.750 -0.3552 0.08137 0.07776 -0.0211 1.0000 0.1181
-6.500 -0.3625 0.07746 0.07391 -0.0306 0.9935 0.1205
-6.250 -0.3322 0.07252 0.06894 -0.0269 0.9898 0.1266
-6.000 -0.4202 0.08101 0.07718 -0.0277 1.0000 0.1214
-5.750 -0.4098 0.07833 0.07452 -0.0251 0.9982 0.1254
-5.500 -0.3710 0.07234 0.06842 -0.0380 0.9885 0.1362
-5.250 -0.3332 0.06736 0.06330 -0.0471 0.9796 0.1499
-5.000 -0.2077 0.04468 0.04064 -0.0672 0.9441 0.1773
-4.750 -0.1845 0.04032 0.03626 -0.0679 0.9345 0.1803
-4.500 -0.1918 0.03460 0.02804 -0.0839 0.9569 0.0806
-4.250 -0.1576 0.03034 0.02325 -0.0867 0.9472 0.0819
-4.000 -0.1163 0.02711 0.01940 -0.0897 0.9397 0.0828
-3.750 -0.0737 0.02477 0.01662 -0.0926 0.9318 0.0852
-3.500 -0.0335 0.02330 0.01477 -0.0948 0.9222 0.0920
-3.250 0.0136 0.02151 0.01279 -0.0981 0.9165 0.0967
-3.000 0.0524 0.02055 0.01173 -0.1000 0.9063 0.1054
-2.750 0.1010 0.01951 0.01075 -0.1036 0.9013 0.1229
-2.500 0.1359 0.01855 0.00994 -0.1046 0.8899 0.1655
-2.250 0.1718 0.01847 0.01004 -0.1059 0.8790 0.2684
-2.000 0.2135 0.01837 0.00982 -0.1083 0.8722 0.3150
-1.750 0.2428 0.01820 0.00962 -0.1084 0.8599 0.3479
-1.500 0.2723 0.01791 0.00934 -0.1086 0.8484 0.3753
-1.250 0.3026 0.01752 0.00904 -0.1089 0.8382 0.4064
-1.000 0.3360 0.01700 0.00862 -0.1096 0.8300 0.4421
-0.750 0.3621 0.01670 0.00846 -0.1091 0.8188 0.4885
-0.500 0.4199 0.01495 0.00797 -0.1143 0.8126 1.0000
-0.250 0.4478 0.01511 0.00783 -0.1141 0.8027 1.0000
0.000 0.4724 0.01536 0.00789 -0.1135 0.7925 1.0000
0.250 0.5016 0.01546 0.00780 -0.1135 0.7853 1.0000
0.500 0.5252 0.01574 0.00797 -0.1128 0.7756 1.0000
0.750 0.5506 0.01600 0.00811 -0.1123 0.7676 1.0000
1.000 0.5772 0.01619 0.00821 -0.1120 0.7602 1.0000
1.250 0.6011 0.01652 0.00849 -0.1114 0.7521 1.0000
1.500 0.6285 0.01669 0.00858 -0.1111 0.7455 1.0000
1.750 0.6516 0.01707 0.00895 -0.1104 0.7376 1.0000
2.000 0.6792 0.01725 0.00910 -0.1102 0.7313 1.0000
2.250 0.7020 0.01766 0.00953 -0.1095 0.7235 1.0000
2.500 0.7296 0.01784 0.00968 -0.1093 0.7173 1.0000
2.750 0.7522 0.01829 0.01018 -0.1085 0.7097 1.0000
3.000 0.7795 0.01850 0.01043 -0.1083 0.7035 1.0000
3.250 0.8023 0.01898 0.01098 -0.1076 0.6962 1.0000
3.500 0.8288 0.01927 0.01131 -0.1073 0.6899 1.0000
3.750 0.8522 0.01976 0.01190 -0.1066 0.6831 1.0000
4.000 0.8774 0.02014 0.01241 -0.1062 0.6765 1.0000
4.250 0.9013 0.02051 0.01289 -0.1054 0.6680 1.0000
4.500 0.9299 0.01988 0.01225 -0.1039 0.6500 1.0000
4.750 0.9579 0.01917 0.01147 -0.1021 0.6273 1.0000
5.000 0.9819 0.01855 0.01081 -0.0998 0.5985 1.0000
5.250 1.0015 0.01807 0.01032 -0.0968 0.5651 1.0000
5.500 1.0105 0.01731 0.00945 -0.0914 0.5003 1.0000
5.750 0.9944 0.01866 0.00941 -0.0830 0.2526 1.0000
6.000 0.9815 0.02197 0.01163 -0.0773 0.1046 1.0000
6.250 0.9859 0.02367 0.01338 -0.0736 0.0893 1.0000
6.500 0.9933 0.02498 0.01484 -0.0703 0.0806 1.0000
6.750 0.9938 0.02654 0.01647 -0.0663 0.0745 1.0000
7.000 0.9998 0.02778 0.01778 -0.0629 0.0690 1.0000
7.250 1.0074 0.02936 0.01928 -0.0598 0.0655 1.0000
7.500 1.0422 0.03175 0.02145 -0.0604 0.0619 1.0000
7.750 1.0751 0.03345 0.02326 -0.0607 0.0572 1.0000
8.000 1.1203 0.03614 0.02599 -0.0626 0.0552 1.0000
8.250 1.1613 0.03928 0.02943 -0.0636 0.0561 1.0000
8.500 1.1927 0.04247 0.03295 -0.0633 0.0573 1.0000
8.750 1.2158 0.04548 0.03629 -0.0621 0.0572 1.0000
9.000 1.2433 0.05044 0.04153 -0.0617 0.0614 1.0000
12.500 0.7754 0.14363 0.13941 -0.0654 0.2247 1.0000
12.750 0.7720 0.14619 0.14198 -0.0659 0.2116 1.0000
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Polar data table (+)
Polar graphs
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