FX 63-143 AIRFOIL (fx63143-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 63-143 AIRFOIL (fx63143-il) Reynolds number: 200,000 Max Cl/Cd: 65.81 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx63143-il-200000-n5.txt Download as CSV file: xf-fx63143-il-200000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.3845 0.09142 0.08801 -0.0417 1.0000 0.0111
-10.000 -0.3887 0.08668 0.08331 -0.0439 1.0000 0.0109
-9.750 -0.3959 0.08121 0.07791 -0.0467 1.0000 0.0107
-9.500 -0.4091 0.07396 0.07072 -0.0515 1.0000 0.0105
-9.250 -0.4348 0.06547 0.06221 -0.0576 1.0000 0.0102
-9.000 -0.4832 0.05564 0.05215 -0.0595 0.9822 0.0096
-8.750 -0.4769 0.05015 0.04637 -0.0641 0.9290 0.0095
-8.500 -0.4560 0.04381 0.03951 -0.0703 0.8948 0.0093
-8.250 -0.4389 0.03831 0.03343 -0.0733 0.8600 0.0091
-7.750 -0.4181 0.03010 0.02398 -0.0713 0.8068 0.0086
-7.500 -0.4051 0.02692 0.02019 -0.0693 0.7871 0.0084
-7.250 -0.3879 0.02439 0.01713 -0.0677 0.7701 0.0083
-7.000 -0.3679 0.02257 0.01494 -0.0664 0.7548 0.0082
-6.750 -0.3468 0.02120 0.01329 -0.0653 0.7412 0.0082
-6.500 -0.3255 0.02019 0.01206 -0.0642 0.7289 0.0082
-6.250 -0.3041 0.01935 0.01107 -0.0632 0.7173 0.0083
-6.000 -0.2822 0.01868 0.01023 -0.0623 0.7072 0.0083
-5.750 -0.2602 0.01808 0.00950 -0.0613 0.6972 0.0084
-5.500 -0.2375 0.01761 0.00893 -0.0605 0.6880 0.0086
-5.250 -0.2148 0.01716 0.00836 -0.0597 0.6790 0.0087
-5.000 -0.1914 0.01680 0.00792 -0.0590 0.6708 0.0089
-4.750 -0.1680 0.01647 0.00749 -0.0583 0.6626 0.0091
-4.500 -0.1441 0.01618 0.00711 -0.0577 0.6549 0.0095
-4.250 -0.1204 0.01583 0.00665 -0.0570 0.6472 0.0110
-4.000 -0.0958 0.01559 0.00623 -0.0563 0.6406 0.0127
-3.750 -0.0704 0.01544 0.00598 -0.0559 0.6332 0.0143
-3.500 -0.0449 0.01534 0.00575 -0.0555 0.6269 0.0159
-3.250 -0.0205 0.01506 0.00536 -0.0550 0.6210 0.0187
-3.000 0.0040 0.01478 0.00501 -0.0545 0.6153 0.0205
-2.750 0.0292 0.01461 0.00475 -0.0541 0.6100 0.0215
-2.500 0.0550 0.01449 0.00456 -0.0538 0.6047 0.0220
-2.250 0.0808 0.01438 0.00440 -0.0535 0.5986 0.0224
-2.000 0.1065 0.01430 0.00423 -0.0532 0.5925 0.0229
-1.750 0.1322 0.01419 0.00411 -0.0529 0.5846 0.0238
-1.500 0.1574 0.01405 0.00398 -0.0525 0.5762 0.0314
-1.250 0.1834 0.01400 0.00388 -0.0522 0.5677 0.0326
-1.000 0.2094 0.01398 0.00376 -0.0519 0.5601 0.0336
-0.750 0.2355 0.01396 0.00368 -0.0516 0.5526 0.0352
-0.500 0.2616 0.01396 0.00361 -0.0514 0.5454 0.0375
-0.250 0.2869 0.01383 0.00351 -0.0510 0.5378 0.0634
0.000 0.3121 0.01370 0.00343 -0.0507 0.5290 0.0812
0.250 0.3382 0.01373 0.00340 -0.0504 0.5202 0.1019
0.500 0.3641 0.01370 0.00337 -0.0502 0.5112 0.1089
0.750 0.3900 0.01362 0.00334 -0.0500 0.5034 0.1446
1.000 0.4159 0.01359 0.00332 -0.0498 0.4948 0.1597
1.250 0.4407 0.01332 0.00331 -0.0496 0.4874 0.2580
1.500 0.4632 0.01256 0.00330 -0.0493 0.4799 0.4807
1.750 0.4772 0.01189 0.00358 -0.0463 0.4729 0.7250
2.000 0.4883 0.01208 0.00409 -0.0417 0.4657 0.8192
2.250 0.5103 0.01226 0.00426 -0.0403 0.4580 0.8457
2.500 0.5339 0.01242 0.00442 -0.0393 0.4514 0.8627
2.750 0.5561 0.01261 0.00461 -0.0380 0.4442 0.8804
3.000 0.5725 0.01288 0.00489 -0.0352 0.4380 0.9036
3.250 0.5900 0.01307 0.00510 -0.0326 0.4313 0.9196
3.500 0.6115 0.01319 0.00519 -0.0314 0.4249 0.9273
3.750 0.6341 0.01328 0.00528 -0.0301 0.4189 0.9347
4.000 0.6551 0.01339 0.00538 -0.0287 0.4123 0.9443
4.250 0.6793 0.01350 0.00549 -0.0278 0.4061 0.9557
4.500 0.7189 0.01362 0.00564 -0.0303 0.3988 0.9641
4.750 0.7473 0.01374 0.00576 -0.0306 0.3906 0.9707
5.000 0.7913 0.01388 0.00594 -0.0343 0.3792 0.9746
5.250 0.8266 0.01403 0.00611 -0.0362 0.3696 0.9782
5.500 0.8518 0.01418 0.00626 -0.0361 0.3605 0.9811
5.750 0.8774 0.01434 0.00644 -0.0361 0.3530 0.9834
6.000 0.9065 0.01452 0.00664 -0.0369 0.3457 0.9850
6.250 0.9348 0.01472 0.00687 -0.0375 0.3382 0.9870
6.500 0.9633 0.01490 0.00713 -0.0382 0.3296 0.9892
6.750 0.9897 0.01512 0.00740 -0.0384 0.3185 0.9918
7.000 1.0141 0.01541 0.00771 -0.0383 0.3046 0.9942
7.250 1.0360 0.01587 0.00810 -0.0380 0.2861 0.9971
7.500 1.0545 0.01634 0.00854 -0.0370 0.2610 1.0000
7.750 1.0532 0.01687 0.00898 -0.0320 0.2382 1.0000
8.000 1.0537 0.01729 0.00937 -0.0274 0.2271 1.0000
8.250 1.0528 0.01768 0.00976 -0.0226 0.2176 1.0000
8.750 1.0597 0.01884 0.01087 -0.0154 0.1801 1.0000
9.000 1.0700 0.01952 0.01157 -0.0134 0.1686 1.0000
9.500 1.0810 0.02173 0.01366 -0.0092 0.1295 1.0000
9.750 1.0917 0.02272 0.01472 -0.0080 0.1146 1.0000
10.000 1.0935 0.02435 0.01629 -0.0064 0.0944 1.0000
10.250 1.0979 0.02598 0.01792 -0.0054 0.0893 1.0000
10.500 1.1067 0.02740 0.01944 -0.0048 0.0840 1.0000
10.750 1.1165 0.02883 0.02098 -0.0044 0.0765 1.0000
11.000 1.1266 0.03029 0.02255 -0.0042 0.0658 1.0000
11.250 1.1282 0.03252 0.02477 -0.0038 0.0610 1.0000
11.500 1.1299 0.03484 0.02711 -0.0036 0.0582 1.0000
11.750 1.1299 0.03739 0.02971 -0.0034 0.0556 1.0000
12.000 1.1336 0.03965 0.03210 -0.0034 0.0532 1.0000
12.250 1.1373 0.04195 0.03456 -0.0035 0.0501 1.0000
12.500 1.1352 0.04488 0.03759 -0.0036 0.0471 1.0000
12.750 1.1477 0.04638 0.03929 -0.0038 0.0406 1.0000
13.000 1.1516 0.04878 0.04177 -0.0040 0.0352 1.0000
13.250 1.1535 0.05144 0.04447 -0.0044 0.0326 1.0000
13.500 1.1539 0.05434 0.04741 -0.0048 0.0304 1.0000
13.750 1.1547 0.05729 0.05047 -0.0053 0.0290 1.0000
14.000 1.1549 0.06039 0.05368 -0.0059 0.0278 1.0000
14.250 1.1550 0.06358 0.05698 -0.0067 0.0268 1.0000
14.500 1.1545 0.06691 0.06041 -0.0075 0.0258 1.0000
14.750 1.1535 0.07037 0.06396 -0.0084 0.0248 1.0000
15.000 1.1513 0.07406 0.06772 -0.0095 0.0237 1.0000
15.250 1.1489 0.07786 0.07160 -0.0106 0.0225 1.0000
15.500 1.1509 0.08110 0.07497 -0.0117 0.0218 1.0000
15.750 1.1534 0.08434 0.07834 -0.0128 0.0208 1.0000
16.000 1.1551 0.08775 0.08187 -0.0140 0.0198 1.0000
16.250 1.1563 0.09127 0.08550 -0.0153 0.0190 1.0000
16.500 1.1567 0.09493 0.08928 -0.0168 0.0183 1.0000
16.750 1.1565 0.09876 0.09320 -0.0183 0.0176 1.0000
17.000 1.1549 0.10283 0.09735 -0.0200 0.0170 1.0000
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Polar data table (+)
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