GOE 124 (MVA H.4) AIRFOIL (goe124-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 124 (MVA H.4) AIRFOIL (goe124-il) Reynolds number: 100,000 Max Cl/Cd: 63.91 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe124-il-100000-n5.txt Download as CSV file: xf-goe124-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 124 (MVA H.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.2746 0.09608 0.09141 -0.0289 1.0000 0.0444
-7.500 -0.2767 0.09427 0.08970 -0.0287 1.0000 0.0459
-7.250 -0.2833 0.09309 0.08864 -0.0288 0.9985 0.0473
-7.000 -0.2438 0.08944 0.08491 -0.0491 0.9790 0.0489
-6.750 -0.2213 0.08420 0.07965 -0.0536 0.9696 0.0494
-6.500 -0.2057 0.07979 0.07525 -0.0520 0.9625 0.0505
-6.250 -0.1838 0.07611 0.07155 -0.0547 0.9517 0.0520
-6.000 -0.1582 0.07252 0.06790 -0.0598 0.9402 0.0547
-5.750 -0.0981 0.06867 0.06372 -0.0814 0.9251 0.0601
-5.500 -0.0883 0.06413 0.05925 -0.0788 0.9164 0.0611
-5.250 -0.0713 0.06110 0.05621 -0.0788 0.9047 0.0627
-5.000 -0.0474 0.05814 0.05318 -0.0814 0.8936 0.0652
-4.750 0.0119 0.05500 0.04949 -0.0959 0.8829 0.0728
-4.500 0.0204 0.05116 0.04581 -0.0935 0.8722 0.0746
-4.250 0.0394 0.04888 0.04353 -0.0934 0.8617 0.0783
-4.000 0.0860 0.04581 0.03999 -0.1015 0.8527 0.0880
-3.750 0.1048 0.04307 0.03729 -0.1013 0.8423 0.0901
-3.500 0.1306 0.04091 0.03504 -0.1025 0.8328 0.0945
-3.250 0.1655 0.03838 0.03222 -0.1060 0.8243 0.1050
-3.000 0.1922 0.03648 0.03024 -0.1070 0.8145 0.1108
-2.750 0.2241 0.03498 0.02847 -0.1091 0.8065 0.1301
-2.500 0.2787 0.02923 0.02159 -0.1130 0.7985 0.0593
-2.250 0.3075 0.02725 0.01945 -0.1138 0.7909 0.0573
-2.000 0.3384 0.02557 0.01748 -0.1146 0.7813 0.0553
-1.750 0.3693 0.02407 0.01561 -0.1151 0.7717 0.0537
-1.500 0.3993 0.02282 0.01399 -0.1152 0.7612 0.0528
-1.250 0.4280 0.02193 0.01285 -0.1152 0.7486 0.0544
-1.000 0.4568 0.02113 0.01178 -0.1151 0.7369 0.0557
-0.750 0.4857 0.02033 0.01072 -0.1149 0.7273 0.0555
-0.500 0.5145 0.01965 0.00987 -0.1148 0.7179 0.0553
-0.250 0.5430 0.01907 0.00913 -0.1147 0.7094 0.0553
0.000 0.5712 0.01856 0.00851 -0.1144 0.7006 0.0556
0.250 0.5991 0.01814 0.00802 -0.1143 0.6916 0.0562
0.500 0.6266 0.01777 0.00757 -0.1139 0.6833 0.0570
0.750 0.6542 0.01754 0.00731 -0.1137 0.6736 0.0593
1.000 0.6817 0.01719 0.00696 -0.1135 0.6655 0.0628
1.250 0.7091 0.01702 0.00677 -0.1133 0.6558 0.0651
1.500 0.7368 0.01692 0.00659 -0.1130 0.6467 0.0676
1.750 0.7645 0.01686 0.00644 -0.1128 0.6373 0.0708
2.000 0.7922 0.01682 0.00639 -0.1126 0.6270 0.0764
2.250 0.8200 0.01676 0.00635 -0.1124 0.6177 0.0948
2.500 0.8399 0.01513 0.00647 -0.1108 0.6081 1.0000
2.750 0.8673 0.01533 0.00652 -0.1105 0.5979 1.0000
3.000 0.8944 0.01552 0.00658 -0.1102 0.5882 1.0000
3.250 0.9213 0.01574 0.00674 -0.1099 0.5765 1.0000
3.500 0.9482 0.01596 0.00691 -0.1097 0.5650 1.0000
3.750 0.9749 0.01619 0.00709 -0.1094 0.5539 1.0000
4.000 1.0015 0.01643 0.00728 -0.1091 0.5431 1.0000
4.250 1.0279 0.01669 0.00754 -0.1088 0.5307 1.0000
4.500 1.0540 0.01695 0.00780 -0.1085 0.5174 1.0000
4.750 1.0798 0.01722 0.00804 -0.1081 0.5032 1.0000
5.000 1.1054 0.01750 0.00830 -0.1076 0.4889 1.0000
5.250 1.1308 0.01781 0.00861 -0.1072 0.4748 1.0000
5.500 1.1560 0.01814 0.00893 -0.1067 0.4619 1.0000
5.750 1.1811 0.01849 0.00927 -0.1062 0.4495 1.0000
6.000 1.2059 0.01887 0.00967 -0.1058 0.4370 1.0000
6.250 1.2305 0.01926 0.01013 -0.1053 0.4244 1.0000
6.500 1.2548 0.01968 0.01059 -0.1048 0.4124 1.0000
6.750 1.2786 0.02011 0.01106 -0.1042 0.4001 1.0000
7.000 1.3019 0.02057 0.01158 -0.1035 0.3869 1.0000
7.250 1.3245 0.02106 0.01210 -0.1028 0.3728 1.0000
7.500 1.3469 0.02158 0.01266 -0.1020 0.3596 1.0000
7.750 1.3687 0.02212 0.01330 -0.1011 0.3454 1.0000
8.000 1.3895 0.02271 0.01399 -0.1002 0.3297 1.0000
8.250 1.4093 0.02335 0.01471 -0.0991 0.3125 1.0000
8.500 1.4283 0.02401 0.01550 -0.0980 0.2918 1.0000
8.750 1.4452 0.02479 0.01635 -0.0965 0.2655 1.0000
9.000 1.4588 0.02578 0.01731 -0.0948 0.2256 1.0000
9.250 1.4655 0.02729 0.01853 -0.0924 0.1846 1.0000
9.500 1.4700 0.02899 0.02003 -0.0898 0.1609 1.0000
9.750 1.4738 0.03066 0.02163 -0.0872 0.1453 1.0000
10.000 1.4757 0.03226 0.02325 -0.0842 0.1334 1.0000
10.250 1.4774 0.03403 0.02504 -0.0817 0.1228 1.0000
10.500 1.4788 0.03593 0.02699 -0.0795 0.1133 1.0000
10.750 1.4836 0.03769 0.02891 -0.0778 0.1039 1.0000
11.000 1.4849 0.03983 0.03114 -0.0762 0.0959 1.0000
11.250 1.4882 0.04193 0.03338 -0.0749 0.0862 1.0000
11.500 1.4906 0.04422 0.03580 -0.0739 0.0754 1.0000
11.750 1.4894 0.04697 0.03861 -0.0729 0.0642 1.0000
12.000 1.4852 0.05018 0.04185 -0.0722 0.0546 1.0000
12.250 1.4787 0.05377 0.04548 -0.0716 0.0476 1.0000
12.500 1.4712 0.05761 0.04937 -0.0712 0.0426 1.0000
12.750 1.4636 0.06157 0.05342 -0.0709 0.0393 1.0000
13.000 1.4565 0.06555 0.05756 -0.0709 0.0365 1.0000
13.250 1.4478 0.06985 0.06195 -0.0710 0.0345 1.0000
13.500 1.4390 0.07423 0.06642 -0.0713 0.0329 1.0000
13.750 1.4329 0.07838 0.07073 -0.0716 0.0312 1.0000
14.000 1.4264 0.08272 0.07521 -0.0722 0.0297 1.0000
14.250 1.4192 0.08726 0.07987 -0.0730 0.0285 1.0000
14.500 1.4109 0.09206 0.08477 -0.0740 0.0276 1.0000
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Polar data table (+)
Polar graphs
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