FX 63-110 AIRFOIL (fx63110-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 63-110 AIRFOIL (fx63110-il) Reynolds number: 200,000 Max Cl/Cd: 87.17 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx63110-il-200000-n5.txt Download as CSV file: xf-fx63110-il-200000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.3581 0.09152 0.08791 -0.0438 1.0000 0.0213
-9.250 -0.3655 0.08766 0.08410 -0.0442 1.0000 0.0213
-9.000 -0.3771 0.08376 0.08029 -0.0443 1.0000 0.0216
-8.750 -0.3807 0.07740 0.07398 -0.0494 0.9966 0.0220
-8.500 -0.4204 0.04156 0.03768 -0.0975 0.9668 0.0224
-8.250 -0.3973 0.02993 0.02476 -0.1134 0.9551 0.0243
-8.000 -0.3672 0.02840 0.02313 -0.1159 0.9490 0.0252
-7.750 -0.3351 0.02682 0.02135 -0.1185 0.9432 0.0263
-7.500 -0.2994 0.02506 0.01929 -0.1218 0.9397 0.0281
-7.250 -0.2675 0.02336 0.01720 -0.1239 0.9326 0.0301
-7.000 -0.2315 0.02130 0.01482 -0.1269 0.9284 0.0317
-6.750 -0.1938 0.02033 0.01377 -0.1296 0.9252 0.0335
-6.500 -0.1610 0.01960 0.01292 -0.1311 0.9184 0.0356
-6.250 -0.1243 0.01856 0.01167 -0.1333 0.9136 0.0376
-5.750 -0.0532 0.01662 0.00937 -0.1370 0.9026 0.0416
-5.500 -0.0170 0.01564 0.00833 -0.1390 0.8970 0.0438
-5.250 0.0180 0.01505 0.00767 -0.1407 0.8907 0.0463
-5.000 0.0515 0.01454 0.00708 -0.1419 0.8832 0.0491
-4.750 0.0865 0.01400 0.00644 -0.1435 0.8770 0.0516
-4.500 0.1177 0.01358 0.00593 -0.1442 0.8685 0.0537
-4.250 0.1516 0.01309 0.00539 -0.1456 0.8617 0.0575
-4.000 0.1817 0.01279 0.00508 -0.1462 0.8531 0.0629
-3.750 0.2141 0.01249 0.00470 -0.1471 0.8459 0.0695
-3.500 0.2439 0.01224 0.00443 -0.1476 0.8371 0.0796
-3.250 0.2753 0.01201 0.00415 -0.1482 0.8287 0.0946
-3.000 0.3047 0.01176 0.00391 -0.1486 0.8177 0.1144
-2.750 0.3350 0.01144 0.00368 -0.1493 0.8078 0.1487
-2.500 0.3668 0.01087 0.00354 -0.1506 0.7990 0.2810
-2.250 0.3964 0.01069 0.00353 -0.1510 0.7906 0.3607
-2.000 0.4260 0.01056 0.00350 -0.1513 0.7828 0.4120
-1.750 0.4547 0.01047 0.00353 -0.1514 0.7744 0.4545
-1.500 0.4835 0.01044 0.00357 -0.1514 0.7667 0.4923
-1.250 0.5117 0.01046 0.00363 -0.1513 0.7582 0.5235
-1.000 0.5402 0.01051 0.00365 -0.1512 0.7506 0.5486
-0.750 0.5683 0.01056 0.00370 -0.1511 0.7420 0.5715
-0.500 0.5966 0.01062 0.00373 -0.1509 0.7344 0.5916
-0.250 0.6243 0.01067 0.00380 -0.1507 0.7256 0.6112
0.000 0.6523 0.01074 0.00383 -0.1505 0.7178 0.6277
0.250 0.6798 0.01079 0.00390 -0.1502 0.7088 0.6397
0.500 0.7076 0.01086 0.00394 -0.1500 0.7005 0.6515
0.750 0.7352 0.01093 0.00401 -0.1498 0.6912 0.6633
1.000 0.7626 0.01100 0.00409 -0.1495 0.6825 0.6738
1.250 0.7901 0.01109 0.00417 -0.1493 0.6731 0.6840
1.500 0.8174 0.01117 0.00426 -0.1490 0.6632 0.6945
1.750 0.8445 0.01127 0.00436 -0.1487 0.6536 0.7046
2.000 0.8713 0.01137 0.00445 -0.1483 0.6411 0.7153
2.250 0.8975 0.01148 0.00454 -0.1477 0.6252 0.7259
2.500 0.9233 0.01160 0.00464 -0.1471 0.6081 0.7360
2.750 0.9494 0.01173 0.00476 -0.1466 0.5928 0.7470
3.000 0.9755 0.01186 0.00491 -0.1461 0.5784 0.7589
3.250 1.0012 0.01200 0.00508 -0.1456 0.5641 0.7709
3.500 1.0266 0.01215 0.00525 -0.1449 0.5488 0.7842
3.750 1.0509 0.01232 0.00541 -0.1441 0.5304 0.8006
4.250 1.0960 0.01267 0.00579 -0.1416 0.4909 0.8461
4.500 1.1140 0.01281 0.00594 -0.1394 0.4706 0.8884
4.750 1.1341 0.01301 0.00610 -0.1377 0.4482 1.0000
5.000 1.1585 0.01345 0.00643 -0.1372 0.4234 1.0000
5.250 1.1824 0.01391 0.00678 -0.1366 0.3972 1.0000
5.500 1.2057 0.01440 0.00716 -0.1360 0.3700 1.0000
5.750 1.2281 0.01495 0.00758 -0.1352 0.3379 1.0000
6.000 1.2495 0.01557 0.00804 -0.1342 0.3028 1.0000
6.250 1.2699 0.01627 0.00857 -0.1332 0.2685 1.0000
6.750 1.3095 0.01777 0.00981 -0.1310 0.2110 1.0000
7.000 1.3289 0.01854 0.01047 -0.1298 0.1878 1.0000
7.250 1.3478 0.01933 0.01116 -0.1286 0.1648 1.0000
7.500 1.3662 0.02013 0.01188 -0.1273 0.1424 1.0000
8.000 1.3998 0.02191 0.01349 -0.1243 0.1033 1.0000
8.250 1.4153 0.02283 0.01437 -0.1226 0.0913 1.0000
8.500 1.4287 0.02378 0.01530 -0.1206 0.0826 1.0000
8.750 1.4423 0.02464 0.01622 -0.1186 0.0761 1.0000
9.000 1.4527 0.02572 0.01729 -0.1162 0.0703 1.0000
9.250 1.4653 0.02665 0.01833 -0.1141 0.0658 1.0000
9.500 1.4762 0.02771 0.01946 -0.1120 0.0618 1.0000
9.750 1.4841 0.02902 0.02080 -0.1097 0.0587 1.0000
10.000 1.4939 0.03023 0.02211 -0.1076 0.0564 1.0000
10.250 1.5037 0.03149 0.02348 -0.1057 0.0541 1.0000
10.500 1.5126 0.03286 0.02494 -0.1039 0.0518 1.0000
10.750 1.5196 0.03444 0.02659 -0.1021 0.0498 1.0000
11.000 1.5235 0.03636 0.02855 -0.1003 0.0480 1.0000
11.250 1.5326 0.03791 0.03024 -0.0989 0.0464 1.0000
11.500 1.5406 0.03959 0.03204 -0.0976 0.0446 1.0000
11.750 1.5479 0.04138 0.03394 -0.0964 0.0429 1.0000
12.000 1.5534 0.04341 0.03604 -0.0953 0.0413 1.0000
12.250 1.5557 0.04582 0.03852 -0.0942 0.0399 1.0000
12.500 1.5599 0.04815 0.04096 -0.0932 0.0386 1.0000
12.750 1.5655 0.05039 0.04335 -0.0925 0.0373 1.0000
13.000 1.5698 0.05281 0.04593 -0.0918 0.0359 1.0000
13.250 1.5729 0.05543 0.04867 -0.0914 0.0346 1.0000
13.500 1.5742 0.05834 0.05167 -0.0910 0.0335 1.0000
13.750 1.5724 0.06171 0.05511 -0.0908 0.0324 1.0000
14.000 1.5735 0.06485 0.05841 -0.0907 0.0314 1.0000
14.250 1.5751 0.06801 0.06175 -0.0908 0.0303 1.0000
14.500 1.5754 0.07143 0.06532 -0.0911 0.0291 1.0000
14.750 1.5746 0.07511 0.06914 -0.0916 0.0281 1.0000
15.000 1.5722 0.07911 0.07325 -0.0924 0.0272 1.0000
15.250 1.5677 0.08352 0.07775 -0.0935 0.0263 1.0000
15.500 1.5648 0.08785 0.08224 -0.0945 0.0255 1.0000
15.750 1.5624 0.09223 0.08684 -0.0958 0.0245 1.0000
16.000 1.5586 0.09692 0.09171 -0.0973 0.0236 1.0000
16.250 1.5541 0.10185 0.09683 -0.0992 0.0228 1.0000
16.500 1.5489 0.10699 0.10211 -0.1013 0.0221 1.0000
16.750 1.5432 0.11235 0.10759 -0.1038 0.0215 1.0000
17.000 1.5362 0.11795 0.11329 -0.1065 0.0210 1.0000
17.250 1.5296 0.12367 0.11921 -0.1092 0.0204 1.0000
17.500 1.5225 0.12960 0.12535 -0.1123 0.0197 1.0000
17.750 1.5147 0.13581 0.13174 -0.1158 0.0190 1.0000
18.000 1.5069 0.14207 0.13817 -0.1195 0.0185 1.0000
18.250 1.4988 0.14857 0.14481 -0.1235 0.0180 1.0000
18.500 1.4906 0.15517 0.15154 -0.1278 0.0176 1.0000
18.750 1.4823 0.16193 0.15842 -0.1323 0.0173 1.0000
19.000 1.4738 0.16884 0.16546 -0.1370 0.0170 1.0000
19.250 1.4660 0.17563 0.17234 -0.1417 0.0167 1.0000
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