GOE 14K AIRFOIL (goe14k-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 14K AIRFOIL (goe14k-il) Reynolds number: 50,000 Max Cl/Cd: 25.45 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe14k-il-50000-n5.txt Download as CSV file: xf-goe14k-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 14K AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.5398 0.11182 0.10508 -0.0386 1.0000 0.0531
-9.750 -0.5533 0.10730 0.10066 -0.0392 1.0000 0.0534
-9.500 -0.5646 0.10329 0.09671 -0.0394 1.0000 0.0529
-9.250 -0.5813 0.09850 0.09201 -0.0402 1.0000 0.0527
-9.000 -0.5991 0.09402 0.08758 -0.0408 1.0000 0.0520
-8.750 -0.6219 0.08978 0.08337 -0.0399 1.0000 0.0518
-8.500 -0.6469 0.08633 0.07994 -0.0370 1.0000 0.0513
-8.250 -0.6733 0.08292 0.07652 -0.0331 1.0000 0.0510
-8.000 -0.6954 0.07918 0.07271 -0.0296 1.0000 0.0509
-7.750 -0.7155 0.07525 0.06865 -0.0258 1.0000 0.0508
-7.500 -0.7328 0.07125 0.06446 -0.0218 1.0000 0.0506
-7.250 -0.7482 0.06732 0.06027 -0.0175 1.0000 0.0515
-7.000 -0.7599 0.06342 0.05604 -0.0131 1.0000 0.0519
-6.750 -0.7676 0.05981 0.05206 -0.0087 1.0000 0.0524
-6.500 -0.7743 0.05606 0.04782 -0.0039 1.0000 0.0534
-6.250 -0.7768 0.05266 0.04388 0.0007 1.0000 0.0543
-6.000 -0.7765 0.04956 0.04022 0.0052 1.0000 0.0560
-5.750 -0.7680 0.04769 0.03827 0.0079 1.0000 0.0585
-5.500 -0.7595 0.04567 0.03591 0.0112 1.0000 0.0615
-5.250 -0.7502 0.04330 0.03300 0.0146 1.0000 0.0644
-5.000 -0.7384 0.04108 0.03020 0.0178 1.0000 0.0682
-4.750 -0.7212 0.03960 0.02861 0.0194 0.9992 0.0734
-4.500 -0.6975 0.03808 0.02649 0.0203 0.9968 0.0797
-4.250 -0.6731 0.03684 0.02519 0.0205 0.9947 0.0871
-4.000 -0.6473 0.03562 0.02373 0.0207 0.9926 0.0961
-3.750 -0.6193 0.03479 0.02260 0.0205 0.9902 0.1066
-3.500 -0.5891 0.03403 0.02179 0.0195 0.9881 0.1171
-3.250 -0.5564 0.03348 0.02110 0.0181 0.9860 0.1312
-3.000 -0.5174 0.03287 0.02033 0.0155 0.9841 0.1439
-2.750 -0.4789 0.03236 0.01971 0.0129 0.9822 0.1613
-2.500 -0.4409 0.03190 0.01935 0.0102 0.9802 0.1953
-2.250 -0.4051 0.03139 0.01927 0.0078 0.9784 0.2796
-1.750 -0.1731 0.03318 0.02297 -0.0288 0.9896 1.0000
-1.500 -0.1460 0.03352 0.02298 -0.0294 0.9863 1.0000
-1.250 -0.1221 0.03367 0.02287 -0.0294 0.9827 1.0000
-1.000 -0.0954 0.03400 0.02294 -0.0299 0.9791 1.0000
-0.750 -0.0709 0.03425 0.02297 -0.0299 0.9754 1.0000
-0.500 -0.0468 0.03450 0.02304 -0.0299 0.9715 1.0000
-0.250 -0.0197 0.03492 0.02326 -0.0305 0.9680 1.0000
0.000 0.0023 0.03512 0.02333 -0.0301 0.9638 1.0000
0.250 0.0268 0.03544 0.02352 -0.0301 0.9597 1.0000
0.500 0.0549 0.03592 0.02388 -0.0309 0.9562 1.0000
0.750 0.0747 0.03610 0.02397 -0.0301 0.9512 1.0000
1.000 0.0996 0.03648 0.02427 -0.0302 0.9468 1.0000
1.250 0.1273 0.03696 0.02469 -0.0310 0.9429 1.0000
1.500 0.1467 0.03720 0.02489 -0.0300 0.9373 1.0000
1.750 0.1727 0.03763 0.02530 -0.0304 0.9327 1.0000
2.000 0.1983 0.03807 0.02573 -0.0307 0.9279 1.0000
2.250 0.2189 0.03841 0.02606 -0.0301 0.9219 1.0000
2.500 0.2476 0.03891 0.02658 -0.0310 0.9170 1.0000
2.750 0.2688 0.03925 0.02695 -0.0304 0.9101 1.0000
3.000 0.3005 0.03963 0.02739 -0.0318 0.9027 1.0000
3.250 0.3270 0.03980 0.02762 -0.0320 0.8920 1.0000
3.500 0.3594 0.03998 0.02788 -0.0332 0.8819 1.0000
3.750 0.3917 0.04022 0.02823 -0.0345 0.8731 1.0000
4.000 0.4135 0.04047 0.02859 -0.0339 0.8632 1.0000
4.250 0.4498 0.04073 0.02902 -0.0358 0.8565 1.0000
4.750 0.4937 0.04116 0.02974 -0.0344 0.8348 1.0000
5.000 0.5303 0.04121 0.03002 -0.0361 0.8264 1.0000
5.250 0.5554 0.04115 0.03015 -0.0356 0.8127 1.0000
5.500 0.5950 0.04028 0.02953 -0.0367 0.7958 1.0000
5.750 0.6162 0.03955 0.02903 -0.0345 0.7722 1.0000
6.000 0.6542 0.03813 0.02792 -0.0346 0.7507 1.0000
6.250 0.6737 0.03716 0.02717 -0.0317 0.7216 1.0000
6.500 0.6855 0.03643 0.02663 -0.0276 0.6840 1.0000
6.750 0.7034 0.03544 0.02584 -0.0241 0.6395 1.0000
7.000 0.7368 0.03374 0.02431 -0.0223 0.5749 1.0000
7.250 0.7991 0.03140 0.02096 -0.0234 0.3957 1.0000
7.500 0.8013 0.03288 0.02188 -0.0193 0.3003 1.0000
7.750 0.8041 0.03446 0.02299 -0.0157 0.2382 1.0000
8.000 0.8122 0.03595 0.02419 -0.0129 0.1996 1.0000
8.250 0.8240 0.03733 0.02538 -0.0107 0.1694 1.0000
8.500 0.8388 0.03861 0.02657 -0.0089 0.1438 1.0000
8.750 0.8551 0.03986 0.02776 -0.0074 0.1228 1.0000
9.000 0.8742 0.04115 0.02902 -0.0063 0.1050 1.0000
9.250 0.8998 0.04239 0.03032 -0.0060 0.0897 1.0000
9.500 0.9290 0.04386 0.03189 -0.0062 0.0767 1.0000
9.750 0.9597 0.04560 0.03368 -0.0066 0.0672 1.0000
10.000 0.9881 0.04755 0.03598 -0.0067 0.0598 1.0000
10.250 1.0148 0.04993 0.03861 -0.0068 0.0551 1.0000
10.500 1.0312 0.05250 0.04163 -0.0052 0.0507 1.0000
10.750 1.0440 0.05507 0.04449 -0.0034 0.0483 1.0000
11.000 1.0520 0.05742 0.04698 -0.0013 0.0464 1.0000
11.250 1.0546 0.06046 0.05027 0.0016 0.0451 1.0000
11.500 1.0452 0.06346 0.05375 0.0060 0.0440 1.0000
11.750 1.0331 0.06669 0.05738 0.0102 0.0433 1.0000
12.000 1.0183 0.07004 0.06107 0.0142 0.0428 1.0000
12.250 0.9992 0.07376 0.06510 0.0179 0.0423 1.0000
12.500 0.9799 0.07761 0.06926 0.0209 0.0423 1.0000
12.750 0.9568 0.08198 0.07384 0.0233 0.0422 1.0000
13.000 0.9326 0.08675 0.07882 0.0248 0.0423 1.0000
13.250 0.9089 0.09182 0.08405 0.0253 0.0425 1.0000
13.500 0.8847 0.09753 0.08990 0.0246 0.0429 1.0000
13.750 0.8564 0.10467 0.09717 0.0224 0.0431 1.0000
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Polar data table (+)
Polar graphs
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