FX 63-100 AIRFOIL (fx63100-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 63-100 AIRFOIL (fx63100-il) Reynolds number: 100,000 Max Cl/Cd: 67.73 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx63100-il-100000-n5.txt Download as CSV file: xf-fx63100-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX 63-100 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 -0.3390 0.09292 0.08802 -0.0400 1.0000 0.0319
-8.250 -0.3458 0.09009 0.08528 -0.0397 1.0000 0.0323
-8.000 -0.3545 0.08762 0.08291 -0.0385 1.0000 0.0321
-7.750 -0.3678 0.08556 0.08096 -0.0366 1.0000 0.0322
-7.500 -0.3849 0.08393 0.07945 -0.0339 1.0000 0.0321
-7.250 -0.3738 0.07850 0.07405 -0.0405 0.9936 0.0321
-7.000 -0.3535 0.07090 0.06644 -0.0518 0.9845 0.0321
-6.750 -0.3287 0.06072 0.05618 -0.0682 0.9745 0.0315
-6.500 -0.2966 0.04867 0.04370 -0.0871 0.9655 0.0314
-6.250 -0.2601 0.03967 0.03398 -0.0997 0.9580 0.0323
-6.000 -0.2134 0.03302 0.02631 -0.1095 0.9549 0.0353
-5.750 -0.1807 0.03015 0.02314 -0.1129 0.9487 0.0373
-5.500 -0.1424 0.02789 0.02049 -0.1165 0.9446 0.0401
-5.250 -0.1011 0.02584 0.01794 -0.1201 0.9417 0.0451
-5.000 -0.0670 0.02391 0.01554 -0.1219 0.9356 0.0481
-4.750 -0.0312 0.02273 0.01432 -0.1242 0.9312 0.0532
-4.500 0.0076 0.02148 0.01281 -0.1264 0.9281 0.0579
-4.250 0.0402 0.02055 0.01171 -0.1275 0.9220 0.0631
-4.000 0.0755 0.01967 0.01083 -0.1292 0.9173 0.0676
-3.750 0.1140 0.01893 0.00995 -0.1312 0.9138 0.0741
-3.500 0.1485 0.01827 0.00934 -0.1328 0.9082 0.0820
-3.250 0.1841 0.01765 0.00865 -0.1344 0.9026 0.0909
-3.000 0.2237 0.01700 0.00797 -0.1369 0.8986 0.1065
-2.750 0.2594 0.01639 0.00745 -0.1388 0.8925 0.1362
-2.500 0.2975 0.01539 0.00707 -0.1417 0.8867 0.2682
-2.250 0.3365 0.01487 0.00695 -0.1440 0.8821 0.4233
-2.000 0.3661 0.01475 0.00705 -0.1440 0.8730 0.4946
-1.750 0.4014 0.01465 0.00700 -0.1449 0.8665 0.5557
-1.500 0.4302 0.01469 0.00702 -0.1447 0.8563 0.5950
-1.000 0.4904 0.01465 0.00695 -0.1447 0.8394 0.6521
-0.750 0.5198 0.01464 0.00692 -0.1445 0.8312 0.6763
-0.500 0.5488 0.01463 0.00688 -0.1444 0.8225 0.6951
-0.250 0.5769 0.01465 0.00687 -0.1441 0.8135 0.7113
0.000 0.6068 0.01463 0.00680 -0.1442 0.8055 0.7276
0.250 0.6332 0.01467 0.00685 -0.1436 0.7956 0.7435
0.500 0.6623 0.01466 0.00680 -0.1435 0.7875 0.7596
0.750 0.6883 0.01470 0.00686 -0.1429 0.7774 0.7758
1.000 0.7148 0.01472 0.00690 -0.1423 0.7680 0.7927
1.250 0.7418 0.01470 0.00688 -0.1417 0.7591 0.8105
1.500 0.7651 0.01473 0.00697 -0.1405 0.7484 0.8295
1.750 0.7891 0.01471 0.00701 -0.1394 0.7385 0.8525
2.000 0.8118 0.01464 0.00698 -0.1379 0.7288 0.8838
2.250 0.8345 0.01454 0.00696 -0.1365 0.7171 1.0000
2.500 0.8654 0.01470 0.00711 -0.1371 0.7056 1.0000
2.750 0.8955 0.01484 0.00721 -0.1375 0.6926 1.0000
3.000 0.9242 0.01497 0.00730 -0.1375 0.6762 1.0000
3.250 0.9523 0.01511 0.00742 -0.1374 0.6586 1.0000
3.500 0.9802 0.01528 0.00756 -0.1372 0.6419 1.0000
3.750 1.0078 0.01549 0.00776 -0.1370 0.6262 1.0000
4.000 1.0350 0.01571 0.00800 -0.1368 0.6099 1.0000
4.250 1.0619 0.01595 0.00824 -0.1365 0.5932 1.0000
4.500 1.0881 0.01620 0.00848 -0.1360 0.5746 1.0000
4.750 1.1131 0.01648 0.00879 -0.1353 0.5518 1.0000
5.000 1.1372 0.01679 0.00904 -0.1344 0.5241 1.0000
5.250 1.1603 0.01718 0.00933 -0.1334 0.4928 1.0000
5.500 1.1828 0.01763 0.00969 -0.1323 0.4615 1.0000
5.750 1.2046 0.01818 0.01014 -0.1312 0.4296 1.0000
6.000 1.2246 0.01884 0.01064 -0.1299 0.3915 1.0000
6.250 1.2431 0.01961 0.01123 -0.1284 0.3461 1.0000
6.500 1.2604 0.02050 0.01190 -0.1268 0.2974 1.0000
6.750 1.2770 0.02150 0.01270 -0.1252 0.2547 1.0000
7.000 1.2936 0.02254 0.01358 -0.1237 0.2197 1.0000
7.250 1.3099 0.02362 0.01454 -0.1221 0.1893 1.0000
7.500 1.3257 0.02474 0.01556 -0.1206 0.1608 1.0000
7.750 1.3405 0.02592 0.01666 -0.1189 0.1352 1.0000
8.250 1.3658 0.02854 0.01914 -0.1150 0.1006 1.0000
8.500 1.3763 0.02987 0.02048 -0.1127 0.0905 1.0000
8.750 1.3858 0.03120 0.02187 -0.1103 0.0835 1.0000
9.000 1.3938 0.03264 0.02337 -0.1078 0.0785 1.0000
9.250 1.4000 0.03428 0.02504 -0.1052 0.0748 1.0000
9.500 1.4097 0.03575 0.02667 -0.1031 0.0714 1.0000
9.750 1.4187 0.03733 0.02841 -0.1011 0.0682 1.0000
10.000 1.4265 0.03904 0.03019 -0.0992 0.0653 1.0000
10.250 1.4338 0.04099 0.03216 -0.0973 0.0626 1.0000
10.500 1.4453 0.04264 0.03402 -0.0958 0.0601 1.0000
10.750 1.4557 0.04443 0.03599 -0.0943 0.0576 1.0000
11.000 1.4644 0.04630 0.03798 -0.0929 0.0550 1.0000
11.250 1.4710 0.04836 0.04009 -0.0916 0.0527 1.0000
11.500 1.4791 0.05054 0.04244 -0.0903 0.0504 1.0000
11.750 1.4861 0.05273 0.04489 -0.0891 0.0479 1.0000
12.000 1.4907 0.05504 0.04742 -0.0880 0.0455 1.0000
12.250 1.4938 0.05750 0.05000 -0.0870 0.0435 1.0000
12.500 1.4968 0.06026 0.05277 -0.0862 0.0416 1.0000
12.750 1.4977 0.06333 0.05619 -0.0854 0.0398 1.0000
13.000 1.4974 0.06661 0.05975 -0.0849 0.0380 1.0000
13.250 1.4956 0.07001 0.06334 -0.0846 0.0363 1.0000
13.500 1.4930 0.07348 0.06694 -0.0846 0.0349 1.0000
13.750 1.4908 0.07705 0.07059 -0.0847 0.0336 1.0000
14.000 1.4850 0.08152 0.07527 -0.0851 0.0325 1.0000
14.250 1.4750 0.08669 0.08079 -0.0860 0.0315 1.0000
14.500 1.4630 0.09230 0.08672 -0.0876 0.0306 1.0000
14.750 1.4502 0.09828 0.09298 -0.0897 0.0298 1.0000
15.000 1.4368 0.10458 0.09954 -0.0924 0.0291 1.0000
15.250 1.4226 0.11135 0.10655 -0.0957 0.0285 1.0000
15.500 1.4072 0.11872 0.11415 -0.0998 0.0281 1.0000
15.750 1.3916 0.12651 0.12215 -0.1045 0.0277 1.0000
16.000 1.3679 0.13688 0.13279 -0.1112 0.0278 1.0000
16.250 1.3239 0.15413 0.15039 -0.1234 0.0291 1.0000
16.500 1.2491 0.18605 0.18243 -0.1455 0.0313 1.0000
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Polar data table (+)
Polar graphs
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