FX 63-143 AIRFOIL (fx63143-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 63-143 AIRFOIL (fx63143-il) Reynolds number: 100,000 Max Cl/Cd: 49.81 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx63143-il-100000-n5.txt Download as CSV file: xf-fx63143-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.3737 0.10363 0.09871 -0.0399 1.0000 0.0211
-10.500 -0.3724 0.09988 0.09500 -0.0410 1.0000 0.0203
-10.000 -0.3847 0.08828 0.08354 -0.0465 1.0000 0.0182
-9.750 -0.3883 0.08373 0.07906 -0.0486 1.0000 0.0179
-9.500 -0.3963 0.07774 0.07313 -0.0522 1.0000 0.0175
-9.250 -0.4130 0.07107 0.06648 -0.0566 1.0000 0.0171
-8.750 -0.4734 0.06109 0.05635 -0.0554 1.0000 0.0159
-8.500 -0.4920 0.05901 0.05429 -0.0518 1.0000 0.0158
-8.250 -0.4872 0.05462 0.04970 -0.0539 0.9716 0.0156
-8.000 -0.4775 0.04990 0.04464 -0.0561 0.9419 0.0154
-7.750 -0.4595 0.04516 0.03944 -0.0587 0.9202 0.0151
-7.500 -0.4382 0.04061 0.03433 -0.0608 0.9007 0.0149
-7.250 -0.4148 0.03665 0.02976 -0.0621 0.8810 0.0148
-7.000 -0.3897 0.03336 0.02588 -0.0629 0.8619 0.0148
-6.750 -0.3632 0.03074 0.02273 -0.0632 0.8439 0.0148
-6.500 -0.3367 0.02854 0.02004 -0.0632 0.8264 0.0150
-6.250 -0.3100 0.02673 0.01780 -0.0630 0.8100 0.0154
-6.000 -0.2831 0.02523 0.01586 -0.0626 0.7947 0.0160
-5.750 -0.2585 0.02404 0.01454 -0.0622 0.7804 0.0165
-5.500 -0.2349 0.02296 0.01323 -0.0615 0.7670 0.0183
-5.250 -0.2129 0.02197 0.01216 -0.0608 0.7550 0.0197
-5.000 -0.1909 0.02106 0.01114 -0.0600 0.7447 0.0220
-4.750 -0.1688 0.02042 0.01048 -0.0592 0.7343 0.0244
-4.500 -0.1444 0.01999 0.00993 -0.0587 0.7259 0.0267
-4.250 -0.1207 0.01962 0.00942 -0.0580 0.7164 0.0314
-4.000 -0.0958 0.01930 0.00885 -0.0574 0.7086 0.0369
-3.750 -0.0724 0.01892 0.00835 -0.0567 0.6996 0.0395
-3.500 -0.0475 0.01864 0.00789 -0.0561 0.6924 0.0425
-3.000 0.0013 0.01808 0.00729 -0.0551 0.6777 0.0591
-2.750 0.0268 0.01798 0.00707 -0.0547 0.6710 0.0710
-2.500 0.0511 0.01772 0.00686 -0.0543 0.6644 0.0963
-2.250 0.0769 0.01755 0.00665 -0.0539 0.6589 0.1177
-2.000 0.0985 0.01701 0.00652 -0.0532 0.6519 0.2434
-1.750 0.1168 0.01614 0.00642 -0.0520 0.6458 0.4285
-1.500 0.1338 0.01550 0.00655 -0.0496 0.6406 0.6048
-1.250 0.1597 0.01563 0.00719 -0.0477 0.6337 0.7282
-1.000 0.1885 0.01585 0.00733 -0.0472 0.6277 0.7648
-0.750 0.2154 0.01608 0.00749 -0.0466 0.6222 0.7943
-0.500 0.2406 0.01636 0.00772 -0.0457 0.6163 0.8201
-0.250 0.2627 0.01661 0.00787 -0.0443 0.6115 0.8441
0.000 0.2891 0.01696 0.00809 -0.0434 0.6075 0.8658
0.250 0.3131 0.01729 0.00840 -0.0423 0.6018 0.8844
0.500 0.3422 0.01760 0.00864 -0.0421 0.5964 0.9035
0.750 0.3766 0.01780 0.00872 -0.0430 0.5917 0.9173
1.000 0.4071 0.01796 0.00886 -0.0435 0.5854 0.9296
1.250 0.4761 0.01807 0.00888 -0.0513 0.5784 0.9503
1.500 0.5291 0.01804 0.00875 -0.0564 0.5726 0.9632
1.750 0.5579 0.01808 0.00880 -0.0570 0.5661 0.9699
2.000 0.5947 0.01802 0.00866 -0.0592 0.5606 0.9740
2.250 0.6278 0.01800 0.00860 -0.0606 0.5540 0.9792
2.500 0.6593 0.01798 0.00857 -0.0618 0.5467 0.9841
2.750 0.6931 0.01791 0.00842 -0.0633 0.5396 0.9879
3.000 0.7220 0.01792 0.00845 -0.0640 0.5305 0.9921
3.250 0.7525 0.01787 0.00835 -0.0649 0.5219 0.9956
3.500 0.7835 0.01784 0.00835 -0.0660 0.5111 0.9999
3.750 0.8016 0.01793 0.00846 -0.0644 0.5028 1.0000
4.000 0.8196 0.01802 0.00856 -0.0628 0.4948 1.0000
4.250 0.8376 0.01813 0.00871 -0.0612 0.4878 1.0000
4.500 0.8553 0.01831 0.00895 -0.0596 0.4813 1.0000
4.750 0.8738 0.01843 0.00908 -0.0581 0.4757 1.0000
5.000 0.8906 0.01863 0.00937 -0.0563 0.4691 1.0000
5.250 0.9073 0.01883 0.00965 -0.0545 0.4628 1.0000
5.500 0.9250 0.01899 0.00984 -0.0528 0.4575 1.0000
5.750 0.9402 0.01925 0.01023 -0.0508 0.4511 1.0000
6.000 0.9557 0.01947 0.01055 -0.0488 0.4449 1.0000
6.250 0.9718 0.01966 0.01079 -0.0468 0.4393 1.0000
6.500 0.9852 0.01994 0.01120 -0.0445 0.4323 1.0000
6.750 0.9996 0.02013 0.01145 -0.0422 0.4259 1.0000
7.000 1.0126 0.02039 0.01183 -0.0397 0.4192 1.0000
7.250 1.0249 0.02065 0.01219 -0.0372 0.4126 1.0000
7.500 1.0385 0.02085 0.01243 -0.0347 0.4070 1.0000
7.750 1.0480 0.02122 0.01297 -0.0318 0.4001 1.0000
8.000 1.0588 0.02152 0.01339 -0.0290 0.3935 1.0000
8.250 1.0701 0.02185 0.01384 -0.0265 0.3864 1.0000
8.500 1.0810 0.02223 0.01438 -0.0239 0.3780 1.0000
8.750 1.0940 0.02260 0.01487 -0.0218 0.3701 1.0000
9.000 1.1067 0.02298 0.01536 -0.0197 0.3608 1.0000
9.250 1.1176 0.02342 0.01589 -0.0174 0.3503 1.0000
9.500 1.1250 0.02394 0.01646 -0.0147 0.3361 1.0000
9.750 1.1294 0.02471 0.01732 -0.0120 0.3163 1.0000
10.000 1.1340 0.02557 0.01817 -0.0095 0.2975 1.0000
10.250 1.1368 0.02668 0.01925 -0.0072 0.2805 1.0000
10.500 1.1386 0.02811 0.02076 -0.0054 0.2577 1.0000
10.750 1.1330 0.03009 0.02263 -0.0035 0.2354 1.0000
11.000 1.1277 0.03239 0.02489 -0.0022 0.2160 1.0000
11.250 1.1212 0.03508 0.02756 -0.0013 0.1871 1.0000
11.500 1.1096 0.03838 0.03073 -0.0007 0.1708 1.0000
11.750 1.1043 0.04137 0.03375 -0.0005 0.1441 1.0000
12.000 1.0913 0.04519 0.03745 -0.0004 0.1328 1.0000
12.250 1.0854 0.04847 0.04074 -0.0005 0.1217 1.0000
12.500 1.0840 0.05138 0.04377 -0.0006 0.1031 1.0000
12.750 1.0745 0.05522 0.04754 -0.0010 0.0956 1.0000
13.000 1.0660 0.05908 0.05136 -0.0016 0.0900 1.0000
13.250 1.0618 0.06259 0.05493 -0.0022 0.0842 1.0000
13.500 1.0625 0.06564 0.05817 -0.0027 0.0747 1.0000
13.750 1.0611 0.06905 0.06166 -0.0035 0.0657 1.0000
14.000 1.0552 0.07310 0.06566 -0.0046 0.0612 1.0000
14.250 1.0498 0.07716 0.06975 -0.0057 0.0577 1.0000
14.500 1.0435 0.08136 0.07391 -0.0069 0.0549 1.0000
14.750 1.0440 0.08466 0.07738 -0.0076 0.0510 1.0000
15.000 1.0448 0.08784 0.08061 -0.0083 0.0476 1.0000
15.250 1.0499 0.09053 0.08346 -0.0088 0.0442 1.0000
15.500 1.0560 0.09309 0.08617 -0.0093 0.0410 1.0000
15.750 1.0613 0.09576 0.08891 -0.0099 0.0390 1.0000
16.000 1.0703 0.09785 0.09114 -0.0102 0.0372 1.0000
16.250 1.0794 0.09998 0.09340 -0.0104 0.0357 1.0000
16.500 1.0865 0.10249 0.09604 -0.0111 0.0343 1.0000
16.750 1.0903 0.10565 0.09931 -0.0123 0.0329 1.0000
17.000 1.0928 0.10903 0.10277 -0.0138 0.0317 1.0000
17.250 1.0970 0.11206 0.10588 -0.0149 0.0304 1.0000
17.500 1.0996 0.11560 0.10966 -0.0162 0.0293 1.0000
17.750 1.0983 0.11995 0.11425 -0.0182 0.0281 1.0000
18.000 1.0946 0.12478 0.11927 -0.0208 0.0269 1.0000
18.250 1.0903 0.12980 0.12443 -0.0236 0.0258 1.0000
18.500 1.0865 0.13473 0.12947 -0.0267 0.0247 1.0000
18.750 1.0845 0.13927 0.13406 -0.0295 0.0236 1.0000
19.000 1.0809 0.14412 0.13899 -0.0323 0.0226 1.0000
19.250 1.0700 0.15114 0.14625 -0.0367 0.0222 1.0000
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