GOE 446 AIRFOIL (goe446-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 446 AIRFOIL (goe446-il) Reynolds number: 100,000 Max Cl/Cd: 56.71 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe446-il-100000-n5.txt Download as CSV file: xf-goe446-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 446 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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.0585 0.09621 0.09086 -0.0995 0.9211 0.0778
-8.250 -0.0575 0.09341 0.08806 -0.1049 0.9124 0.0784
-8.000 -0.0590 0.09089 0.08555 -0.1069 0.9004 0.0785
-7.750 -0.0520 0.08766 0.08231 -0.1099 0.8918 0.0786
-7.250 -0.0270 0.07698 0.07153 -0.1120 0.8827 0.0603
-7.000 -0.0175 0.07491 0.06945 -0.1109 0.8745 0.0580
-6.500 -0.0048 0.06367 0.05803 -0.1235 0.8582 0.0524
-6.250 0.0145 0.06134 0.05565 -0.1252 0.8539 0.0531
-6.000 0.0305 0.05842 0.05265 -0.1276 0.8480 0.0536
-5.500 0.0693 0.04532 0.03890 -0.1399 0.8368 0.0519
-5.250 0.0850 0.04151 0.03482 -0.1414 0.8299 0.0517
-5.000 0.1077 0.03699 0.02985 -0.1439 0.8249 0.0517
-4.750 0.1362 0.03235 0.02452 -0.1467 0.8216 0.0520
-4.500 0.1626 0.03037 0.02223 -0.1476 0.8174 0.0528
-4.250 0.1846 0.02973 0.02150 -0.1471 0.8113 0.0540
-4.000 0.2141 0.02847 0.01999 -0.1480 0.8074 0.0558
-3.750 0.2471 0.02658 0.01767 -0.1494 0.8045 0.0575
-3.500 0.2711 0.02528 0.01601 -0.1490 0.7981 0.0587
-3.250 0.2999 0.02415 0.01462 -0.1492 0.7920 0.0602
-3.000 0.3344 0.02333 0.01370 -0.1503 0.7876 0.0622
-2.750 0.3573 0.02287 0.01314 -0.1494 0.7796 0.0646
-2.500 0.3871 0.02218 0.01227 -0.1496 0.7740 0.0690
-2.250 0.4202 0.02176 0.01181 -0.1505 0.7704 0.0745
-2.000 0.4424 0.02151 0.01152 -0.1496 0.7637 0.0806
-1.750 0.4701 0.02117 0.01109 -0.1494 0.7583 0.0903
-1.500 0.5019 0.02082 0.01070 -0.1501 0.7543 0.1030
-1.250 0.5267 0.02078 0.01068 -0.1496 0.7484 0.1150
-1.000 0.5520 0.02073 0.01061 -0.1492 0.7423 0.1274
-0.750 0.5828 0.02059 0.01045 -0.1497 0.7378 0.1453
-0.500 0.6087 0.02050 0.01035 -0.1494 0.7322 0.1579
-0.250 0.6328 0.02044 0.01030 -0.1488 0.7257 0.1670
0.000 0.6627 0.02017 0.01000 -0.1490 0.7211 0.1750
0.250 0.6885 0.02009 0.00991 -0.1486 0.7152 0.1836
0.500 0.7123 0.02005 0.00992 -0.1478 0.7083 0.1949
0.750 0.7434 0.01982 0.00968 -0.1483 0.7034 0.2130
1.250 0.7929 0.01955 0.00983 -0.1474 0.6900 0.3344
1.750 0.8397 0.01844 0.00994 -0.1451 0.6771 1.0000
2.000 0.8680 0.01850 0.00986 -0.1450 0.6709 1.0000
2.250 0.8917 0.01872 0.00999 -0.1442 0.6635 1.0000
2.500 0.9164 0.01888 0.01007 -0.1436 0.6561 1.0000
2.750 0.9443 0.01898 0.01007 -0.1436 0.6500 1.0000
3.000 0.9648 0.01929 0.01036 -0.1423 0.6415 1.0000
3.250 0.9948 0.01931 0.01028 -0.1426 0.6358 1.0000
3.500 1.0130 0.01969 0.01067 -0.1410 0.6263 1.0000
3.750 1.0418 0.01973 0.01064 -0.1410 0.6199 1.0000
4.000 1.0607 0.02010 0.01102 -0.1395 0.6106 1.0000
4.250 1.0883 0.02021 0.01106 -0.1394 0.6041 1.0000
4.500 1.1082 0.02058 0.01146 -0.1382 0.5956 1.0000
4.750 1.1344 0.02074 0.01158 -0.1378 0.5887 1.0000
5.000 1.1552 0.02109 0.01194 -0.1367 0.5805 1.0000
5.250 1.1801 0.02130 0.01214 -0.1362 0.5733 1.0000
5.500 1.2023 0.02164 0.01249 -0.1353 0.5660 1.0000
5.750 1.2249 0.02196 0.01283 -0.1345 0.5588 1.0000
6.000 1.2504 0.02221 0.01307 -0.1342 0.5526 1.0000
6.250 1.2693 0.02268 0.01359 -0.1328 0.5449 1.0000
6.500 1.2970 0.02287 0.01376 -0.1328 0.5393 1.0000
6.750 1.3135 0.02342 0.01440 -0.1311 0.5315 1.0000
7.000 1.3378 0.02366 0.01463 -0.1306 0.5242 1.0000
7.250 1.3524 0.02415 0.01517 -0.1284 0.5147 1.0000
7.500 1.3702 0.02439 0.01537 -0.1266 0.5034 1.0000
7.750 1.3859 0.02469 0.01562 -0.1245 0.4907 1.0000
8.000 1.3945 0.02531 0.01629 -0.1215 0.4784 1.0000
8.250 1.4100 0.02583 0.01683 -0.1196 0.4689 1.0000
8.500 1.4268 0.02638 0.01742 -0.1181 0.4611 1.0000
8.750 1.4437 0.02695 0.01807 -0.1166 0.4538 1.0000
9.000 1.4573 0.02763 0.01883 -0.1146 0.4458 1.0000
9.250 1.4737 0.02822 0.01947 -0.1131 0.4381 1.0000
9.500 1.4845 0.02904 0.02039 -0.1109 0.4294 1.0000
9.750 1.4990 0.02973 0.02115 -0.1092 0.4213 1.0000
10.000 1.5075 0.03067 0.02220 -0.1068 0.4120 1.0000
10.250 1.5154 0.03167 0.02328 -0.1044 0.4017 1.0000
10.500 1.5231 0.03263 0.02427 -0.1020 0.3901 1.0000
10.750 1.5237 0.03407 0.02582 -0.0990 0.3769 1.0000
11.000 1.5229 0.03570 0.02756 -0.0962 0.3626 1.0000
11.250 1.5212 0.03751 0.02945 -0.0935 0.3467 1.0000
11.500 1.5186 0.03951 0.03149 -0.0909 0.3289 1.0000
11.750 1.5148 0.04174 0.03375 -0.0885 0.3088 1.0000
12.000 1.5098 0.04417 0.03616 -0.0862 0.2860 1.0000
12.250 1.5030 0.04688 0.03876 -0.0840 0.2636 1.0000
12.500 1.4955 0.04984 0.04164 -0.0820 0.2432 1.0000
12.750 1.4881 0.05296 0.04471 -0.0802 0.2262 1.0000
13.000 1.4811 0.05617 0.04789 -0.0787 0.2116 1.0000
13.250 1.4742 0.05950 0.05121 -0.0773 0.1985 1.0000
13.500 1.4675 0.06292 0.05464 -0.0762 0.1868 1.0000
14.000 1.4572 0.06974 0.06153 -0.0745 0.1668 1.0000
14.250 1.4527 0.07320 0.06504 -0.0739 0.1586 1.0000
14.500 1.4488 0.07668 0.06858 -0.0734 0.1504 1.0000
14.750 1.4446 0.08027 0.07226 -0.0731 0.1421 1.0000
15.000 1.4377 0.08426 0.07627 -0.0729 0.1336 1.0000
15.250 1.4345 0.08790 0.08001 -0.0729 0.1249 1.0000
15.500 1.4290 0.09188 0.08405 -0.0730 0.1166 1.0000
15.750 1.4210 0.09631 0.08851 -0.0734 0.1064 1.0000
16.000 1.4143 0.10064 0.09288 -0.0739 0.0940 1.0000
16.250 1.4085 0.10488 0.09717 -0.0745 0.0773 1.0000
16.500 1.3984 0.10979 0.10201 -0.0753 0.0592 1.0000
16.750 1.3875 0.11487 0.10698 -0.0764 0.0497 1.0000
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Polar data table (+)
Polar graphs
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