FX 63-100 AIRFOIL (fx63100-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 63-100 AIRFOIL (fx63100-il) Reynolds number: 200,000 Max Cl/Cd: 92.86 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx63100-il-200000.txt Download as CSV file: xf-fx63100-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3713 0.09455 0.09118 -0.0419 1.0000 0.0500
-8.250 -0.3848 0.09258 0.08931 -0.0405 1.0000 0.0501
-8.000 -0.4038 0.09108 0.08791 -0.0381 1.0000 0.0502
-7.750 -0.3883 0.08657 0.08340 -0.0341 1.0000 0.0516
-7.500 -0.3999 0.08556 0.08247 -0.0302 1.0000 0.0520
-7.250 -0.4144 0.08466 0.08164 -0.0265 1.0000 0.0525
-7.000 -0.3979 0.08133 0.07832 -0.0299 0.9967 0.0542
-6.750 -0.3707 0.07564 0.07261 -0.0400 0.9900 0.0579
-6.500 -0.3284 0.05855 0.05526 -0.0757 0.9783 0.0629
-6.250 -0.3070 0.05922 0.05606 -0.0707 0.9753 0.0657
-6.000 -0.2557 0.04728 0.04330 -0.0961 0.9668 0.0755
-5.750 -0.2089 0.03340 0.02845 -0.1077 0.9642 0.0516
-5.500 -0.1651 0.02850 0.02308 -0.1129 0.9620 0.0478
-5.250 -0.1181 0.02498 0.01886 -0.1180 0.9603 0.0493
-5.000 -0.0798 0.02211 0.01546 -0.1209 0.9558 0.0507
-4.750 -0.0431 0.02060 0.01392 -0.1234 0.9515 0.0553
-4.500 -0.0016 0.01920 0.01224 -0.1261 0.9487 0.0592
-4.250 0.0406 0.01775 0.01062 -0.1291 0.9467 0.0643
-4.000 0.0733 0.01697 0.00980 -0.1301 0.9400 0.0688
-3.750 0.1132 0.01633 0.00903 -0.1323 0.9362 0.0748
-3.500 0.1554 0.01517 0.00796 -0.1353 0.9340 0.0824
-3.250 0.2000 0.01430 0.00710 -0.1387 0.9322 0.0933
-3.000 0.2348 0.01360 0.00646 -0.1402 0.9247 0.1084
-2.750 0.2805 0.01251 0.00558 -0.1440 0.9210 0.1596
-2.500 0.3281 0.01121 0.00523 -0.1487 0.9180 0.4288
-2.250 0.3603 0.01099 0.00521 -0.1493 0.9091 0.4983
-2.000 0.3986 0.01085 0.00511 -0.1509 0.9039 0.5538
-1.750 0.4287 0.01087 0.00517 -0.1509 0.8949 0.5928
-1.500 0.4632 0.01081 0.00513 -0.1517 0.8884 0.6264
-1.250 0.4913 0.01085 0.00516 -0.1513 0.8784 0.6504
-1.000 0.5227 0.01083 0.00513 -0.1515 0.8710 0.6732
-0.750 0.5499 0.01088 0.00517 -0.1510 0.8607 0.6948
-0.500 0.5770 0.01092 0.00523 -0.1504 0.8516 0.7143
-0.250 0.6049 0.01094 0.00524 -0.1498 0.8427 0.7338
0.000 0.6307 0.01099 0.00531 -0.1491 0.8325 0.7514
0.250 0.6587 0.01100 0.00529 -0.1487 0.8240 0.7665
0.500 0.6846 0.01103 0.00532 -0.1480 0.8136 0.7806
0.750 0.7108 0.01105 0.00536 -0.1473 0.8037 0.7946
1.000 0.7381 0.01105 0.00534 -0.1468 0.7948 0.8091
1.250 0.7627 0.01106 0.00540 -0.1458 0.7837 0.8240
1.500 0.7879 0.01107 0.00543 -0.1449 0.7733 0.8394
1.750 0.8130 0.01104 0.00539 -0.1439 0.7625 0.8560
2.000 0.8364 0.01097 0.00533 -0.1425 0.7488 0.8756
2.250 0.8567 0.01086 0.00525 -0.1404 0.7341 0.9003
2.500 0.8761 0.01068 0.00512 -0.1382 0.7204 0.9541
2.750 0.9089 0.01076 0.00519 -0.1393 0.7066 1.0000
3.000 0.9399 0.01089 0.00528 -0.1400 0.6925 1.0000
3.250 0.9697 0.01104 0.00539 -0.1403 0.6779 1.0000
3.500 0.9982 0.01117 0.00547 -0.1403 0.6611 1.0000
3.750 1.0258 0.01132 0.00556 -0.1401 0.6425 1.0000
4.000 1.0526 0.01149 0.00569 -0.1397 0.6226 1.0000
4.250 1.0786 0.01168 0.00583 -0.1392 0.5997 1.0000
4.500 1.1037 0.01189 0.00598 -0.1385 0.5731 1.0000
4.750 1.1283 0.01215 0.00616 -0.1377 0.5450 1.0000
5.000 1.1525 0.01247 0.00638 -0.1369 0.5162 1.0000
5.250 1.1760 0.01285 0.00667 -0.1360 0.4846 1.0000
5.500 1.1988 0.01331 0.00701 -0.1350 0.4519 1.0000
5.750 1.2211 0.01383 0.00741 -0.1340 0.4185 1.0000
6.000 1.2424 0.01442 0.00786 -0.1329 0.3825 1.0000
6.250 1.2628 0.01508 0.00838 -0.1316 0.3382 1.0000
6.500 1.2810 0.01594 0.00898 -0.1301 0.2846 1.0000
6.750 1.2970 0.01705 0.00977 -0.1284 0.2304 1.0000
7.000 1.3122 0.01830 0.01071 -0.1267 0.1775 1.0000
7.250 1.3250 0.01982 0.01187 -0.1246 0.1239 1.0000
7.500 1.3375 0.02135 0.01317 -0.1224 0.0962 1.0000
7.750 1.3513 0.02270 0.01446 -0.1203 0.0840 1.0000
8.000 1.3630 0.02419 0.01590 -0.1180 0.0770 1.0000
8.250 1.3793 0.02525 0.01705 -0.1162 0.0721 1.0000
8.500 1.3928 0.02652 0.01834 -0.1142 0.0679 1.0000
8.750 1.4046 0.02809 0.01992 -0.1119 0.0646 1.0000
9.000 1.4200 0.02915 0.02111 -0.1101 0.0617 1.0000
9.250 1.4342 0.03030 0.02233 -0.1082 0.0586 1.0000
9.500 1.4477 0.03180 0.02380 -0.1065 0.0557 1.0000
9.750 1.4651 0.03361 0.02569 -0.1052 0.0532 1.0000
10.000 1.4790 0.03480 0.02707 -0.1034 0.0507 1.0000
10.250 1.4922 0.03613 0.02850 -0.1017 0.0482 1.0000
10.500 1.5061 0.03772 0.03009 -0.1002 0.0459 1.0000
10.750 1.5247 0.04019 0.03270 -0.0994 0.0434 1.0000
11.000 1.5341 0.04175 0.03449 -0.0973 0.0415 1.0000
11.250 1.5446 0.04359 0.03650 -0.0955 0.0397 1.0000
11.500 1.5540 0.04543 0.03844 -0.0939 0.0380 1.0000
11.750 1.5734 0.04935 0.04244 -0.0938 0.0356 1.0000
12.000 1.5701 0.05126 0.04465 -0.0909 0.0347 1.0000
12.250 1.5688 0.05381 0.04749 -0.0886 0.0337 1.0000
12.500 1.5675 0.05686 0.05082 -0.0867 0.0328 1.0000
12.750 1.5647 0.06007 0.05427 -0.0850 0.0319 1.0000
13.000 1.5615 0.06336 0.05777 -0.0837 0.0311 1.0000
13.250 1.5563 0.06681 0.06141 -0.0826 0.0304 1.0000
13.500 1.5510 0.07044 0.06520 -0.0820 0.0298 1.0000
13.750 1.5472 0.07454 0.06942 -0.0816 0.0290 1.0000
14.000 1.5309 0.08072 0.07586 -0.0817 0.0286 1.0000
14.250 1.5086 0.08747 0.08291 -0.0826 0.0284 1.0000
14.500 1.4882 0.09372 0.08942 -0.0841 0.0284 1.0000
15.000 1.4418 0.10781 0.10400 -0.0901 0.0283 1.0000
15.250 1.1995 0.18317 0.18052 -0.1428 0.0409 1.0000
15.500 1.1906 0.19367 0.19098 -0.1488 0.0423 1.0000
15.750 1.1942 0.19871 0.19603 -0.1510 0.0435 1.0000
16.000 0.9528 0.21175 0.20953 -0.1390 0.0653 1.0000
16.250 0.9338 0.21885 0.21659 -0.1455 0.0639 1.0000
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Polar data table (+)
Polar graphs
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