GOE 610 B AIRFOIL (goe610b-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 610 B AIRFOIL (goe610b-il) Reynolds number: 100,000 Max Cl/Cd: 61.25 at α=7.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe610b-il-100000.txt Download as CSV file: xf-goe610b-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 610 B 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 -0.3110 0.10990 0.10513 -0.0374 1.0000 0.0575
-8.500 -0.3222 0.10931 0.10467 -0.0370 1.0000 0.0576
-8.250 -0.3355 0.10871 0.10421 -0.0360 1.0000 0.0577
-8.000 -0.3044 0.09924 0.09466 -0.0336 1.0000 0.0593
-7.750 -0.3047 0.09668 0.09217 -0.0314 1.0000 0.0606
-7.500 -0.3155 0.09549 0.09108 -0.0283 1.0000 0.0614
-7.250 -0.3336 0.09496 0.09067 -0.0242 1.0000 0.0617
-7.000 -0.3488 0.09414 0.08994 -0.0209 1.0000 0.0625
-6.750 -0.3601 0.09294 0.08881 -0.0188 1.0000 0.0634
-6.500 -0.3696 0.09152 0.08746 -0.0172 1.0000 0.0647
-6.250 -0.3773 0.09000 0.08600 -0.0167 1.0000 0.0665
-6.000 -0.3378 0.08757 0.08338 -0.0376 0.9912 0.0700
-5.750 -0.3289 0.08146 0.07738 -0.0323 0.9875 0.0718
-5.500 -0.3011 0.07729 0.07317 -0.0362 0.9810 0.0757
-5.250 -0.2439 0.07283 0.06839 -0.0549 0.9706 0.0831
-5.000 -0.2324 0.06837 0.06403 -0.0521 0.9630 0.0859
-4.500 -0.1627 0.06042 0.05585 -0.0642 0.9461 0.1003
-4.250 -0.1166 0.05691 0.05200 -0.0732 0.9370 0.1112
-4.000 -0.0909 0.05326 0.04839 -0.0744 0.9299 0.1182
-3.750 -0.0579 0.05003 0.04500 -0.0784 0.9210 0.1299
-3.500 -0.0179 0.04671 0.04147 -0.0834 0.9144 0.1433
-3.250 0.0130 0.04410 0.03870 -0.0860 0.9050 0.1574
-3.000 0.0549 0.04153 0.03586 -0.0905 0.8995 0.1844
-2.750 0.0822 0.03909 0.03337 -0.0916 0.8904 0.2017
-2.500 0.1190 0.03665 0.03081 -0.0942 0.8849 0.2319
-2.250 0.1424 0.03506 0.02916 -0.0942 0.8754 0.2750
-1.750 0.1928 0.01418 0.00882 -0.0894 0.8404 0.3951
-1.500 0.2087 0.01286 0.00756 -0.0874 0.8324 0.4315
-1.250 0.3017 0.02792 0.02001 -0.1016 0.8475 0.1669
-1.000 0.3379 0.02623 0.01778 -0.1019 0.8411 0.1375
-0.750 0.3695 0.02490 0.01628 -0.1023 0.8348 0.1317
-0.500 0.3974 0.02419 0.01526 -0.1018 0.8268 0.1270
-0.250 0.4333 0.02333 0.01428 -0.1029 0.8227 0.1299
0.000 0.4525 0.02326 0.01412 -0.1014 0.8130 0.1319
0.250 0.4879 0.02250 0.01323 -0.1021 0.8083 0.1320
0.500 0.5088 0.02238 0.01308 -0.1008 0.7986 0.1335
0.750 0.5448 0.02166 0.01227 -0.1014 0.7931 0.1368
1.000 0.5654 0.02148 0.01217 -0.1000 0.7829 0.1410
1.250 0.6007 0.02091 0.01159 -0.1006 0.7778 0.1537
1.500 0.6207 0.02102 0.01178 -0.0994 0.7685 0.1645
1.750 0.6541 0.02050 0.01133 -0.0998 0.7633 0.1949
2.000 0.7180 0.01880 0.01113 -0.1073 0.7555 1.0000
2.250 0.7465 0.01881 0.01099 -0.1068 0.7491 1.0000
2.500 0.7664 0.01919 0.01132 -0.1053 0.7400 1.0000
2.750 0.7970 0.01899 0.01103 -0.1050 0.7332 1.0000
3.000 0.8164 0.01931 0.01136 -0.1033 0.7230 1.0000
3.250 0.8428 0.01925 0.01125 -0.1024 0.7144 1.0000
3.500 0.8694 0.01914 0.01112 -0.1015 0.7051 1.0000
3.750 0.8914 0.01928 0.01127 -0.1001 0.6948 1.0000
4.000 0.9196 0.01914 0.01111 -0.0995 0.6866 1.0000
4.250 0.9429 0.01929 0.01130 -0.0984 0.6771 1.0000
4.500 0.9664 0.01945 0.01153 -0.0973 0.6677 1.0000
4.750 0.9963 0.01928 0.01135 -0.0969 0.6594 1.0000
5.000 1.0182 0.01943 0.01157 -0.0955 0.6473 1.0000
5.250 1.0420 0.01947 0.01166 -0.0942 0.6346 1.0000
5.500 1.0664 0.01949 0.01176 -0.0930 0.6214 1.0000
5.750 1.0909 0.01957 0.01189 -0.0919 0.6080 1.0000
6.000 1.1149 0.01967 0.01205 -0.0907 0.5933 1.0000
6.250 1.1382 0.01978 0.01222 -0.0893 0.5768 1.0000
6.500 1.1613 0.01987 0.01237 -0.0879 0.5586 1.0000
6.750 1.1849 0.01992 0.01242 -0.0865 0.5391 1.0000
7.000 1.2026 0.02017 0.01280 -0.0843 0.5172 1.0000
7.250 1.2231 0.02028 0.01295 -0.0825 0.4958 1.0000
7.500 1.2381 0.02040 0.01320 -0.0798 0.4694 1.0000
7.750 1.2513 0.02043 0.01325 -0.0768 0.4375 1.0000
8.000 1.2608 0.02063 0.01336 -0.0733 0.3969 1.0000
8.250 1.2682 0.02126 0.01371 -0.0696 0.3572 1.0000
8.500 1.2756 0.02222 0.01447 -0.0663 0.3245 1.0000
8.750 1.2806 0.02332 0.01546 -0.0627 0.2918 1.0000
9.000 1.2821 0.02441 0.01653 -0.0587 0.2528 1.0000
9.250 1.2750 0.02574 0.01767 -0.0535 0.1975 1.0000
9.500 1.2579 0.02808 0.01938 -0.0479 0.1396 1.0000
9.750 1.2397 0.03113 0.02206 -0.0428 0.1110 1.0000
10.000 1.2312 0.03383 0.02462 -0.0390 0.0912 1.0000
10.250 1.2321 0.03587 0.02665 -0.0365 0.0786 1.0000
10.500 1.2356 0.03778 0.02856 -0.0343 0.0710 1.0000
10.750 1.2417 0.03976 0.03055 -0.0322 0.0654 1.0000
11.000 1.2491 0.04159 0.03236 -0.0305 0.0606 1.0000
11.250 1.2668 0.04358 0.03434 -0.0290 0.0562 1.0000
11.500 1.2918 0.04552 0.03643 -0.0279 0.0531 1.0000
11.750 1.3165 0.04778 0.03879 -0.0271 0.0503 1.0000
12.000 1.3512 0.05177 0.04284 -0.0278 0.0468 1.0000
12.250 1.3543 0.05431 0.04573 -0.0257 0.0459 1.0000
12.500 1.3585 0.05753 0.04931 -0.0239 0.0455 1.0000
12.750 1.3569 0.06100 0.05312 -0.0220 0.0453 1.0000
13.000 1.3503 0.06470 0.05719 -0.0202 0.0452 1.0000
13.250 1.3395 0.06866 0.06146 -0.0186 0.0453 1.0000
13.500 1.3266 0.07285 0.06594 -0.0175 0.0455 1.0000
13.750 1.3101 0.07740 0.07076 -0.0168 0.0457 1.0000
14.000 1.2919 0.08233 0.07595 -0.0167 0.0459 1.0000
14.250 1.2736 0.08757 0.08141 -0.0172 0.0462 1.0000
14.500 1.2529 0.09332 0.08737 -0.0184 0.0464 1.0000
14.750 1.2333 0.09946 0.09370 -0.0201 0.0468 1.0000
15.000 1.2161 0.10626 0.10064 -0.0221 0.0472 1.0000
15.250 1.1937 0.11214 0.10676 -0.0254 0.0476 1.0000
15.500 1.1581 0.12090 0.11575 -0.0316 0.0484 1.0000
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Polar data table (+)
Polar graphs
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