FX 63-143 AIRFOIL (fx63143-il) Xfoil prediction polar at RE=200,000 Ncrit=9
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Airfoil: FX 63-143 AIRFOIL (fx63143-il) Reynolds number: 200,000 Max Cl/Cd: 72.8 at α=7.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx63143-il-200000.txt Download as CSV file: xf-fx63143-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: FX 63-143 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
------ -------- --------- --------- -------- -------- --------
-10.250 -0.3643 0.10051 0.09716 -0.0398 1.0000 0.0410
-10.000 -0.3811 0.09330 0.09003 -0.0463 1.0000 0.0418
-9.750 -0.4023 0.08465 0.08144 -0.0549 1.0000 0.0419
-9.500 -0.3768 0.08680 0.08363 -0.0464 1.0000 0.0429
-9.250 -0.3778 0.08328 0.08016 -0.0474 1.0000 0.0437
-9.000 -0.3862 0.07836 0.07531 -0.0505 1.0000 0.0442
-8.750 -0.4059 0.07261 0.06960 -0.0546 1.0000 0.0443
-8.500 -0.4300 0.06896 0.06598 -0.0542 1.0000 0.0442
-8.250 -0.4586 0.06695 0.06404 -0.0504 0.9998 0.0441
-8.000 -0.4642 0.05843 0.05495 -0.0590 0.9616 0.0472
-7.750 -0.4298 0.05508 0.05170 -0.0626 0.9456 0.0489
-7.500 -0.4047 0.04996 0.04623 -0.0683 0.9252 0.0539
-7.250 -0.3738 0.04557 0.04142 -0.0735 0.9034 0.0599
-6.500 -0.3123 0.02925 0.02281 -0.0720 0.8355 0.0298
-6.250 -0.2912 0.02590 0.01892 -0.0704 0.8185 0.0257
-6.000 -0.2677 0.02318 0.01561 -0.0688 0.8034 0.0230
-5.750 -0.2422 0.02147 0.01361 -0.0680 0.7897 0.0220
-5.500 -0.2156 0.01989 0.01165 -0.0671 0.7776 0.0213
-5.250 -0.1914 0.01890 0.01052 -0.0662 0.7648 0.0212
-5.000 -0.1690 0.01791 0.00949 -0.0652 0.7533 0.0215
-4.750 -0.1473 0.01712 0.00860 -0.0640 0.7437 0.0221
-4.500 -0.1272 0.01639 0.00782 -0.0627 0.7332 0.0231
-4.250 -0.1057 0.01582 0.00717 -0.0616 0.7246 0.0248
-4.000 -0.0820 0.01556 0.00691 -0.0608 0.7153 0.0276
-3.750 -0.0573 0.01535 0.00658 -0.0602 0.7075 0.0317
-3.500 -0.0328 0.01517 0.00626 -0.0595 0.6992 0.0362
-3.250 -0.0085 0.01488 0.00585 -0.0590 0.6928 0.0436
-3.000 0.0151 0.01460 0.00565 -0.0584 0.6852 0.0505
-2.750 0.0412 0.01453 0.00548 -0.0581 0.6787 0.0641
-2.500 0.0666 0.01443 0.00532 -0.0577 0.6722 0.0717
-2.250 0.0912 0.01423 0.00517 -0.0572 0.6649 0.0972
-2.000 0.1176 0.01418 0.00502 -0.0570 0.6583 0.1115
-1.750 0.1412 0.01393 0.00490 -0.0564 0.6496 0.1567
-1.500 0.1630 0.01330 0.00472 -0.0557 0.6428 0.2964
-1.250 0.1864 0.01300 0.00466 -0.0551 0.6349 0.3727
-1.000 0.2114 0.01279 0.00456 -0.0547 0.6279 0.4291
-0.750 0.2358 0.01257 0.00452 -0.0543 0.6209 0.4957
-0.500 0.2595 0.01228 0.00451 -0.0535 0.6135 0.5738
-0.250 0.2742 0.01201 0.00491 -0.0498 0.6076 0.7509
0.000 0.2915 0.01233 0.00545 -0.0464 0.5994 0.8230
0.250 0.3149 0.01256 0.00557 -0.0450 0.5922 0.8470
0.500 0.3382 0.01268 0.00567 -0.0440 0.5845 0.8609
0.750 0.3626 0.01283 0.00574 -0.0429 0.5776 0.8694
1.000 0.3860 0.01297 0.00583 -0.0418 0.5707 0.8804
1.250 0.4085 0.01310 0.00591 -0.0405 0.5635 0.8919
1.500 0.4333 0.01327 0.00597 -0.0395 0.5580 0.9000
1.750 0.4541 0.01342 0.00614 -0.0377 0.5508 0.9125
2.000 0.4821 0.01366 0.00635 -0.0368 0.5444 0.9309
2.250 0.5102 0.01380 0.00643 -0.0366 0.5383 0.9426
2.500 0.5589 0.01388 0.00650 -0.0407 0.5312 0.9501
2.750 0.6585 0.01401 0.00653 -0.0550 0.5230 0.9719
3.000 0.7052 0.01395 0.00650 -0.0592 0.5161 0.9788
3.250 0.7759 0.01377 0.00626 -0.0684 0.5090 0.9933
3.500 0.8250 0.01359 0.00614 -0.0733 0.5023 1.0000
3.750 0.8453 0.01364 0.00622 -0.0721 0.4970 1.0000
4.000 0.8661 0.01371 0.00626 -0.0711 0.4922 1.0000
4.250 0.8860 0.01378 0.00640 -0.0698 0.4867 1.0000
4.500 0.9061 0.01387 0.00654 -0.0686 0.4816 1.0000
4.750 0.9264 0.01395 0.00663 -0.0675 0.4768 1.0000
5.000 0.9464 0.01406 0.00677 -0.0662 0.4718 1.0000
5.250 0.9655 0.01417 0.00698 -0.0648 0.4661 1.0000
5.500 0.9849 0.01427 0.00712 -0.0634 0.4606 1.0000
5.750 1.0044 0.01440 0.00728 -0.0621 0.4558 1.0000
6.000 1.0226 0.01452 0.00753 -0.0605 0.4498 1.0000
6.250 1.0408 0.01465 0.00772 -0.0589 0.4438 1.0000
6.500 1.0587 0.01479 0.00791 -0.0572 0.4381 1.0000
6.750 1.0750 0.01491 0.00814 -0.0553 0.4300 1.0000
7.000 1.0912 0.01506 0.00828 -0.0532 0.4228 1.0000
7.250 1.1055 0.01520 0.00853 -0.0509 0.4130 1.0000
7.500 1.1192 0.01538 0.00873 -0.0484 0.4039 1.0000
7.750 1.1328 0.01556 0.00903 -0.0460 0.3952 1.0000
8.000 1.1455 0.01576 0.00930 -0.0434 0.3869 1.0000
8.250 1.1560 0.01595 0.00958 -0.0403 0.3757 1.0000
8.500 1.1645 0.01616 0.00983 -0.0369 0.3636 1.0000
8.750 1.1704 0.01640 0.01009 -0.0331 0.3510 1.0000
9.000 1.1740 0.01670 0.01038 -0.0289 0.3364 1.0000
9.250 1.1811 0.01704 0.01078 -0.0256 0.3167 1.0000
9.500 1.1860 0.01752 0.01121 -0.0221 0.2971 1.0000
9.750 1.1885 0.01824 0.01184 -0.0185 0.2761 1.0000
10.000 1.1926 0.01914 0.01267 -0.0156 0.2415 1.0000
10.250 1.1930 0.02036 0.01379 -0.0127 0.2197 1.0000
10.500 1.1935 0.02178 0.01514 -0.0103 0.1857 1.0000
10.750 1.1908 0.02358 0.01687 -0.0082 0.1670 1.0000
11.000 1.1888 0.02558 0.01881 -0.0066 0.1385 1.0000
11.250 1.1815 0.02819 0.02133 -0.0053 0.1275 1.0000
11.500 1.1862 0.03007 0.02334 -0.0047 0.1053 1.0000
11.750 1.1772 0.03320 0.02635 -0.0040 0.0949 1.0000
12.000 1.1666 0.03665 0.02977 -0.0036 0.0884 1.0000
12.250 1.1612 0.03977 0.03300 -0.0033 0.0785 1.0000
12.500 1.1602 0.04255 0.03578 -0.0033 0.0642 1.0000
12.750 1.1486 0.04645 0.03965 -0.0033 0.0594 1.0000
13.000 1.1343 0.05069 0.04388 -0.0035 0.0561 1.0000
13.250 1.1257 0.05438 0.04761 -0.0035 0.0532 1.0000
13.500 1.1240 0.05743 0.05075 -0.0035 0.0499 1.0000
13.750 1.1244 0.06007 0.05333 -0.0032 0.0474 1.0000
14.000 1.1318 0.06212 0.05547 -0.0029 0.0452 1.0000
14.250 1.1398 0.06430 0.05779 -0.0031 0.0431 1.0000
14.500 1.1468 0.06659 0.06016 -0.0034 0.0408 1.0000
14.750 1.1531 0.06890 0.06242 -0.0038 0.0388 1.0000
15.000 1.1594 0.07150 0.06523 -0.0045 0.0370 1.0000
15.250 1.1648 0.07420 0.06807 -0.0053 0.0352 1.0000
15.500 1.1704 0.07686 0.07082 -0.0061 0.0337 1.0000
15.750 1.1751 0.07965 0.07366 -0.0069 0.0322 1.0000
16.000 1.1862 0.08129 0.07534 -0.0064 0.0305 1.0000
16.250 1.1911 0.08418 0.07843 -0.0071 0.0295 1.0000
16.500 1.1937 0.08744 0.08187 -0.0080 0.0281 1.0000
16.750 1.1934 0.09118 0.08577 -0.0095 0.0265 1.0000
17.000 1.1934 0.09489 0.08958 -0.0110 0.0251 1.0000
17.250 1.1931 0.09851 0.09327 -0.0120 0.0235 1.0000
17.500 1.1872 0.10325 0.09825 -0.0134 0.0222 1.0000
17.750 1.1812 0.10829 0.10351 -0.0159 0.0213 1.0000
18.000 1.1753 0.11338 0.10881 -0.0182 0.0206 1.0000
18.250 1.1682 0.11875 0.11439 -0.0208 0.0200 1.0000
18.500 1.1598 0.12445 0.12028 -0.0238 0.0194 1.0000
18.750 1.1504 0.13047 0.12649 -0.0272 0.0190 1.0000
19.000 1.1385 0.13719 0.13341 -0.0311 0.0188 1.0000
19.250 1.1244 0.14457 0.14099 -0.0357 0.0187 1.0000
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