FX 63-110 AIRFOIL (fx63110-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 63-110 AIRFOIL (fx63110-il) Reynolds number: 200,000 Max Cl/Cd: 90.9 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx63110-il-200000.txt Download as CSV file: xf-fx63110-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: FX 63-110 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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3491 0.08945 0.08613 -0.0371 1.0000 0.0614
-8.000 -0.3653 0.08818 0.08494 -0.0341 1.0000 0.0628
-7.750 -0.3864 0.08729 0.08415 -0.0305 1.0000 0.0632
-7.500 -0.3793 0.06891 0.06564 -0.0718 0.9841 0.0678
-7.250 -0.3615 0.07420 0.07110 -0.0515 0.9853 0.0697
-7.000 -0.3374 0.07139 0.06827 -0.0542 0.9799 0.0723
-6.750 -0.3049 0.05262 0.04893 -0.0937 0.9646 0.0813
-6.500 -0.2640 0.03656 0.03177 -0.1088 0.9606 0.0553
-6.250 -0.2279 0.03160 0.02626 -0.1141 0.9554 0.0552
-6.000 -0.1884 0.02737 0.02149 -0.1187 0.9513 0.0549
-5.750 -0.1453 0.02428 0.01782 -0.1230 0.9487 0.0569
-5.500 -0.1045 0.02223 0.01564 -0.1265 0.9466 0.0595
-5.250 -0.0711 0.02091 0.01415 -0.1279 0.9404 0.0615
-5.000 -0.0317 0.01981 0.01283 -0.1302 0.9365 0.0651
-4.750 0.0106 0.01879 0.01155 -0.1329 0.9340 0.0673
-4.500 0.0523 0.01717 0.00997 -0.1360 0.9323 0.0718
-4.250 0.0858 0.01650 0.00926 -0.1371 0.9258 0.0762
-4.000 0.1253 0.01571 0.00838 -0.1391 0.9217 0.0805
-3.750 0.1666 0.01473 0.00750 -0.1420 0.9187 0.0892
-3.500 0.2046 0.01394 0.00674 -0.1440 0.9133 0.1002
-3.250 0.2430 0.01314 0.00600 -0.1462 0.9065 0.1231
-3.000 0.2891 0.01172 0.00516 -0.1506 0.9020 0.2427
-2.750 0.3221 0.01124 0.00512 -0.1518 0.8924 0.4118
-2.500 0.3580 0.01101 0.00502 -0.1531 0.8862 0.4694
-2.250 0.3863 0.01104 0.00513 -0.1529 0.8764 0.5128
-2.000 0.4191 0.01107 0.00515 -0.1534 0.8696 0.5495
-1.750 0.4458 0.01119 0.00528 -0.1528 0.8595 0.5779
-1.500 0.4761 0.01126 0.00532 -0.1528 0.8521 0.6038
-1.250 0.5030 0.01134 0.00539 -0.1523 0.8424 0.6247
-1.000 0.5312 0.01139 0.00544 -0.1519 0.8345 0.6444
-0.750 0.5579 0.01145 0.00552 -0.1513 0.8253 0.6637
-0.500 0.5852 0.01153 0.00558 -0.1507 0.8169 0.6827
-0.250 0.6123 0.01159 0.00564 -0.1502 0.8082 0.7021
0.000 0.6389 0.01166 0.00571 -0.1496 0.7994 0.7190
0.250 0.6662 0.01168 0.00572 -0.1490 0.7910 0.7325
0.500 0.6922 0.01173 0.00579 -0.1484 0.7815 0.7453
0.750 0.7201 0.01175 0.00578 -0.1480 0.7735 0.7584
1.000 0.7456 0.01180 0.00586 -0.1473 0.7633 0.7714
1.250 0.7730 0.01183 0.00587 -0.1468 0.7547 0.7844
1.500 0.7993 0.01186 0.00591 -0.1462 0.7445 0.7971
1.750 0.8247 0.01188 0.00597 -0.1454 0.7343 0.8091
2.000 0.8508 0.01186 0.00593 -0.1447 0.7235 0.8220
2.250 0.8757 0.01181 0.00587 -0.1436 0.7100 0.8356
2.500 0.8995 0.01177 0.00587 -0.1424 0.6957 0.8501
2.750 0.9230 0.01175 0.00589 -0.1412 0.6827 0.8664
3.000 0.9457 0.01174 0.00591 -0.1398 0.6705 0.8860
3.250 0.9665 0.01169 0.00588 -0.1380 0.6585 0.9139
3.500 0.9913 0.01160 0.00580 -0.1371 0.6458 1.0000
3.750 1.0229 0.01176 0.00594 -0.1380 0.6307 1.0000
4.000 1.0528 0.01194 0.00606 -0.1385 0.6146 1.0000
4.250 1.0811 0.01212 0.00621 -0.1386 0.5963 1.0000
4.500 1.1082 0.01230 0.00637 -0.1384 0.5766 1.0000
4.750 1.1348 0.01252 0.00654 -0.1381 0.5570 1.0000
5.000 1.1606 0.01277 0.00672 -0.1376 0.5364 1.0000
5.250 1.1854 0.01304 0.00695 -0.1370 0.5127 1.0000
5.500 1.2093 0.01338 0.00718 -0.1362 0.4876 1.0000
5.750 1.2325 0.01377 0.00749 -0.1353 0.4604 1.0000
6.000 1.2552 0.01422 0.00785 -0.1344 0.4328 1.0000
6.250 1.2773 0.01472 0.00826 -0.1334 0.4056 1.0000
6.500 1.2988 0.01526 0.00871 -0.1323 0.3774 1.0000
6.750 1.3194 0.01584 0.00921 -0.1311 0.3442 1.0000
7.000 1.3381 0.01655 0.00977 -0.1297 0.3050 1.0000
7.250 1.3547 0.01743 0.01044 -0.1280 0.2631 1.0000
7.500 1.3694 0.01849 0.01126 -0.1262 0.2240 1.0000
7.750 1.3835 0.01962 0.01221 -0.1242 0.1862 1.0000
8.000 1.3952 0.02093 0.01328 -0.1220 0.1486 1.0000
8.250 1.4056 0.02231 0.01445 -0.1195 0.1187 1.0000
8.500 1.4144 0.02369 0.01569 -0.1168 0.1011 1.0000
8.750 1.4216 0.02503 0.01701 -0.1138 0.0907 1.0000
9.000 1.4248 0.02669 0.01858 -0.1105 0.0839 1.0000
9.250 1.4359 0.02784 0.01985 -0.1082 0.0787 1.0000
9.500 1.4433 0.02931 0.02132 -0.1057 0.0744 1.0000
9.750 1.4505 0.03105 0.02308 -0.1033 0.0708 1.0000
10.000 1.4623 0.03234 0.02449 -0.1015 0.0676 1.0000
10.250 1.4729 0.03377 0.02598 -0.0997 0.0646 1.0000
10.500 1.4826 0.03559 0.02776 -0.0980 0.0617 1.0000
10.750 1.4956 0.03730 0.02956 -0.0965 0.0594 1.0000
11.000 1.5070 0.03876 0.03118 -0.0950 0.0569 1.0000
11.250 1.5176 0.04033 0.03283 -0.0936 0.0546 1.0000
11.500 1.5285 0.04205 0.03456 -0.0924 0.0524 1.0000
11.750 1.5440 0.04426 0.03684 -0.0914 0.0500 1.0000
12.000 1.5516 0.04605 0.03884 -0.0899 0.0483 1.0000
12.250 1.5594 0.04800 0.04095 -0.0886 0.0464 1.0000
12.500 1.5673 0.04999 0.04303 -0.0874 0.0447 1.0000
12.750 1.5789 0.05212 0.04513 -0.0866 0.0428 1.0000
13.000 1.5866 0.05504 0.04827 -0.0855 0.0412 1.0000
13.250 1.5868 0.05771 0.05121 -0.0843 0.0400 1.0000
13.500 1.5884 0.06056 0.05427 -0.0833 0.0387 1.0000
13.750 1.5895 0.06351 0.05739 -0.0826 0.0376 1.0000
14.000 1.5909 0.06640 0.06040 -0.0820 0.0365 1.0000
14.250 1.5969 0.06926 0.06329 -0.0816 0.0353 1.0000
14.500 1.5932 0.07408 0.06833 -0.0812 0.0343 1.0000
14.750 1.5796 0.07854 0.07309 -0.0814 0.0338 1.0000
15.000 1.5656 0.08355 0.07840 -0.0820 0.0333 1.0000
15.250 1.5505 0.08902 0.08416 -0.0832 0.0329 1.0000
15.500 1.5342 0.09497 0.09038 -0.0850 0.0324 1.0000
15.750 1.5170 0.10146 0.09713 -0.0875 0.0321 1.0000
16.000 1.4977 0.10861 0.10455 -0.0907 0.0320 1.0000
16.250 1.4750 0.11687 0.11308 -0.0951 0.0320 1.0000
16.500 1.4503 0.12606 0.12254 -0.1007 0.0320 1.0000
16.750 1.4208 0.13697 0.13371 -0.1079 0.0322 1.0000
17.000 1.3867 0.14999 0.14699 -0.1173 0.0327 1.0000
17.250 1.3465 0.16605 0.16327 -0.1292 0.0336 1.0000
17.500 1.2979 0.18754 0.18490 -0.1446 0.0348 1.0000
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