GOE 57 AIRFOIL (goe57-il) Xfoil prediction polar at RE=200,000 Ncrit=9
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Airfoil: GOE 57 AIRFOIL (goe57-il) Reynolds number: 200,000 Max Cl/Cd: 82.43 at α=3° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe57-il-200000.txt Download as CSV file: xf-goe57-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 57 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-6.750 -0.3318 0.08983 0.08676 -0.0179 1.0000 0.0350
-6.500 -0.3379 0.08827 0.08525 -0.0160 1.0000 0.0354
-6.250 -0.3419 0.08654 0.08357 -0.0148 1.0000 0.0360
-6.000 -0.3433 0.08461 0.08166 -0.0143 1.0000 0.0367
-5.750 -0.3148 0.08053 0.07754 -0.0213 0.9963 0.0390
-5.500 -0.2388 0.07681 0.07359 -0.0458 0.9893 0.0426
-5.250 -0.2048 0.07023 0.06694 -0.0539 0.9854 0.0431
-5.000 -0.1903 0.06534 0.06209 -0.0536 0.9827 0.0441
-4.750 -0.1683 0.06196 0.05870 -0.0553 0.9774 0.0455
-4.500 -0.1336 0.05849 0.05516 -0.0606 0.9735 0.0485
-4.250 -0.0578 0.05543 0.05171 -0.0764 0.9695 0.0546
-4.000 -0.0201 0.05011 0.04620 -0.0827 0.9633 0.0555
-3.750 0.0060 0.04584 0.04201 -0.0852 0.9598 0.0571
-3.500 0.0434 0.04292 0.03903 -0.0892 0.9558 0.0603
-3.250 0.0877 0.03996 0.03589 -0.0945 0.9486 0.0653
-3.000 0.1511 0.03573 0.03125 -0.1035 0.9450 0.0704
-2.750 0.1883 0.03300 0.02851 -0.1067 0.9377 0.0732
-2.500 0.2414 0.03123 0.02621 -0.1117 0.9322 0.0839
-2.250 0.2729 0.02823 0.02330 -0.1139 0.9263 0.0863
-2.000 0.3065 0.02651 0.02149 -0.1155 0.9186 0.0915
-1.750 0.3435 0.02465 0.01934 -0.1174 0.9104 0.1002
-1.500 0.3795 0.02361 0.01799 -0.1186 0.9015 0.1126
-1.250 0.4057 0.02177 0.01620 -0.1187 0.8899 0.1170
-1.000 0.4350 0.02063 0.01490 -0.1189 0.8787 0.1301
-0.750 0.4629 0.01964 0.01382 -0.1189 0.8674 0.1471
-0.250 0.5298 0.01602 0.00913 -0.1175 0.8442 0.0801
0.000 0.5575 0.01489 0.00780 -0.1168 0.8304 0.0762
0.250 0.5849 0.01408 0.00679 -0.1161 0.8160 0.0750
0.500 0.6118 0.01348 0.00607 -0.1153 0.8012 0.0758
0.750 0.6384 0.01313 0.00561 -0.1146 0.7850 0.0801
1.000 0.6648 0.01279 0.00516 -0.1137 0.7666 0.0827
1.250 0.6905 0.01219 0.00458 -0.1129 0.7457 0.0859
1.500 0.7165 0.01189 0.00425 -0.1121 0.7243 0.0918
1.750 0.7424 0.01162 0.00396 -0.1114 0.7008 0.1007
2.000 0.7682 0.01146 0.00376 -0.1107 0.6758 0.1215
2.250 0.7911 0.00970 0.00364 -0.1095 0.6510 1.0000
2.500 0.8163 0.00994 0.00358 -0.1086 0.6232 1.0000
2.750 0.8411 0.01021 0.00364 -0.1077 0.5939 1.0000
3.000 0.8655 0.01050 0.00374 -0.1068 0.5618 1.0000
3.250 0.8895 0.01081 0.00388 -0.1059 0.5242 1.0000
3.500 0.9125 0.01121 0.00404 -0.1049 0.4810 1.0000
3.750 0.9346 0.01172 0.00427 -0.1037 0.4353 1.0000
4.000 0.9562 0.01232 0.00458 -0.1026 0.3891 1.0000
4.250 0.9774 0.01299 0.00498 -0.1015 0.3429 1.0000
4.500 0.9994 0.01363 0.00539 -0.1005 0.3054 1.0000
4.750 1.0220 0.01422 0.00580 -0.0996 0.2826 1.0000
5.000 1.0455 0.01470 0.00616 -0.0989 0.2645 1.0000
5.250 1.0691 0.01515 0.00653 -0.0983 0.2492 1.0000
5.500 1.0927 0.01558 0.00690 -0.0976 0.2373 1.0000
5.750 1.1160 0.01603 0.00727 -0.0969 0.2261 1.0000
6.000 1.1396 0.01644 0.00765 -0.0963 0.2148 1.0000
6.250 1.1631 0.01684 0.00803 -0.0957 0.2027 1.0000
6.500 1.1865 0.01725 0.00849 -0.0950 0.1937 1.0000
6.750 1.2091 0.01773 0.00895 -0.0942 0.1828 1.0000
7.000 1.2314 0.01822 0.00941 -0.0934 0.1694 1.0000
7.250 1.2546 0.01863 0.00984 -0.0927 0.1539 1.0000
7.500 1.2790 0.01895 0.01022 -0.0921 0.1310 1.0000
8.000 1.3078 0.02196 0.01256 -0.0882 0.0311 1.0000
8.250 1.3266 0.02291 0.01362 -0.0867 0.0283 1.0000
8.500 1.3447 0.02387 0.01476 -0.0852 0.0264 1.0000
8.750 1.3607 0.02495 0.01605 -0.0834 0.0249 1.0000
9.000 1.3742 0.02616 0.01743 -0.0813 0.0242 1.0000
9.250 1.3841 0.02751 0.01894 -0.0788 0.0236 1.0000
9.500 1.3897 0.02899 0.02054 -0.0757 0.0233 1.0000
9.750 1.3921 0.03059 0.02224 -0.0723 0.0230 1.0000
10.000 1.3944 0.03233 0.02409 -0.0690 0.0228 1.0000
10.250 1.3969 0.03420 0.02606 -0.0661 0.0227 1.0000
10.500 1.4007 0.03614 0.02809 -0.0635 0.0227 1.0000
10.750 1.4062 0.03811 0.03018 -0.0611 0.0228 1.0000
11.000 1.4132 0.04022 0.03237 -0.0590 0.0227 1.0000
11.250 1.4230 0.04271 0.03492 -0.0570 0.0223 1.0000
11.500 1.4408 0.04585 0.03814 -0.0557 0.0219 1.0000
11.750 1.4541 0.04802 0.04047 -0.0542 0.0220 1.0000
12.000 1.4635 0.04995 0.04256 -0.0524 0.0223 1.0000
12.250 1.4691 0.05194 0.04478 -0.0505 0.0227 1.0000
12.500 1.4730 0.05450 0.04769 -0.0484 0.0237 1.0000
12.750 1.4711 0.05868 0.05234 -0.0462 0.0254 1.0000
13.000 1.4666 0.06322 0.05723 -0.0444 0.0269 1.0000
13.250 1.3079 0.06045 0.05456 -0.0313 0.0237 1.0000
13.500 1.2934 0.06547 0.05990 -0.0301 0.0246 1.0000
13.750 1.2757 0.07076 0.06547 -0.0295 0.0252 1.0000
14.000 1.2557 0.07610 0.07106 -0.0294 0.0258 1.0000
14.250 1.2336 0.08152 0.07671 -0.0297 0.0262 1.0000
14.500 1.2098 0.08698 0.08238 -0.0306 0.0265 1.0000
14.750 1.1825 0.09226 0.08785 -0.0319 0.0267 1.0000
15.000 1.1525 0.09734 0.09313 -0.0335 0.0268 1.0000
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Polar data table (+)
Polar graphs
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