FX 63-110 AIRFOIL (fx63110-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 63-110 AIRFOIL (fx63110-il) Reynolds number: 500,000 Max Cl/Cd: 105.8 at α=3° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx63110-il-500000-n5.txt Download as CSV file: xf-fx63110-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.000 -0.7626 0.04609 0.04333 -0.0745 1.0000 0.0108
-11.750 -0.7759 0.03425 0.03110 -0.0929 0.9952 0.0108
-11.500 -0.7467 0.02882 0.02525 -0.1051 0.9902 0.0110
-11.250 -0.7158 0.02592 0.02204 -0.1109 0.9870 0.0114
-11.000 -0.6858 0.02375 0.01965 -0.1148 0.9835 0.0118
-10.750 -0.6554 0.02239 0.01817 -0.1174 0.9796 0.0123
-10.500 -0.6223 0.02131 0.01697 -0.1200 0.9769 0.0127
-10.250 -0.5935 0.02031 0.01584 -0.1215 0.9718 0.0133
-10.000 -0.5623 0.01926 0.01464 -0.1233 0.9673 0.0139
-9.750 -0.5324 0.01830 0.01352 -0.1247 0.9618 0.0146
-9.500 -0.5023 0.01748 0.01260 -0.1260 0.9554 0.0154
-9.250 -0.4711 0.01697 0.01206 -0.1272 0.9495 0.0161
-9.000 -0.4384 0.01644 0.01146 -0.1287 0.9434 0.0170
-8.750 -0.4021 0.01576 0.01065 -0.1309 0.9392 0.0180
-8.500 -0.3659 0.01510 0.00984 -0.1331 0.9329 0.0189
-8.250 -0.3266 0.01452 0.00923 -0.1359 0.9277 0.0201
-8.000 -0.2879 0.01418 0.00884 -0.1384 0.9216 0.0212
-7.750 -0.2494 0.01375 0.00832 -0.1409 0.9138 0.0226
-7.500 -0.2126 0.01331 0.00774 -0.1430 0.9047 0.0237
-7.250 -0.1779 0.01272 0.00704 -0.1447 0.8948 0.0249
-7.000 -0.1467 0.01239 0.00666 -0.1457 0.8844 0.0261
-6.750 -0.1161 0.01214 0.00633 -0.1463 0.8747 0.0273
-6.500 -0.0866 0.01185 0.00595 -0.1468 0.8646 0.0286
-6.250 -0.0575 0.01160 0.00561 -0.1471 0.8555 0.0297
-6.000 -0.0284 0.01138 0.00529 -0.1474 0.8468 0.0306
-5.750 0.0008 0.01090 0.00473 -0.1479 0.8385 0.0320
-5.500 0.0300 0.01057 0.00433 -0.1483 0.8301 0.0337
-5.250 0.0591 0.01031 0.00402 -0.1486 0.8221 0.0350
-5.000 0.0882 0.01010 0.00374 -0.1488 0.8144 0.0363
-4.750 0.1172 0.00991 0.00348 -0.1491 0.8066 0.0378
-4.500 0.1461 0.00975 0.00325 -0.1493 0.7978 0.0393
-4.250 0.1748 0.00960 0.00302 -0.1494 0.7874 0.0403
-4.000 0.2038 0.00939 0.00273 -0.1496 0.7763 0.0433
-3.750 0.2327 0.00925 0.00253 -0.1497 0.7661 0.0475
-3.500 0.2618 0.00912 0.00238 -0.1499 0.7576 0.0526
-3.000 0.3200 0.00886 0.00214 -0.1504 0.7420 0.0774
-2.500 0.3781 0.00867 0.00195 -0.1508 0.7266 0.1050
-2.250 0.4070 0.00859 0.00186 -0.1510 0.7188 0.1211
-2.000 0.4369 0.00837 0.00177 -0.1515 0.7112 0.1679
-1.750 0.4677 0.00798 0.00172 -0.1525 0.7036 0.2957
-1.500 0.4971 0.00787 0.00172 -0.1529 0.6957 0.3476
-1.250 0.5261 0.00781 0.00173 -0.1531 0.6879 0.3892
-1.000 0.5552 0.00775 0.00173 -0.1533 0.6803 0.4191
-0.750 0.5839 0.00774 0.00174 -0.1534 0.6721 0.4410
-0.500 0.6129 0.00771 0.00178 -0.1535 0.6640 0.4714
-0.250 0.6414 0.00772 0.00184 -0.1536 0.6560 0.5033
0.000 0.6700 0.00775 0.00190 -0.1536 0.6475 0.5311
0.250 0.6981 0.00782 0.00197 -0.1536 0.6390 0.5548
0.500 0.7264 0.00786 0.00204 -0.1535 0.6300 0.5740
0.750 0.7543 0.00794 0.00211 -0.1534 0.6205 0.5901
1.000 0.7818 0.00805 0.00218 -0.1532 0.6073 0.6021
1.250 0.8090 0.00817 0.00225 -0.1529 0.5900 0.6108
1.500 0.8360 0.00831 0.00232 -0.1527 0.5705 0.6187
1.750 0.8630 0.00844 0.00242 -0.1524 0.5529 0.6272
2.000 0.8903 0.00858 0.00252 -0.1522 0.5386 0.6353
2.250 0.9172 0.00873 0.00264 -0.1519 0.5213 0.6433
2.500 0.9432 0.00896 0.00278 -0.1515 0.4982 0.6504
2.750 0.9694 0.00918 0.00293 -0.1511 0.4760 0.6578
3.000 0.9956 0.00941 0.00310 -0.1508 0.4573 0.6653
3.250 1.0212 0.00968 0.00330 -0.1503 0.4350 0.6735
3.500 1.0466 0.00999 0.00352 -0.1499 0.4102 0.6820
3.750 1.0719 0.01029 0.00375 -0.1494 0.3880 0.6906
4.000 1.0980 0.01053 0.00397 -0.1491 0.3716 0.6996
4.250 1.1235 0.01082 0.00421 -0.1487 0.3498 0.7112
4.500 1.1476 0.01123 0.00451 -0.1480 0.3163 0.7236
4.750 1.1711 0.01170 0.00485 -0.1474 0.2827 0.7362
5.000 1.1939 0.01225 0.00524 -0.1466 0.2451 0.7494
5.250 1.2168 0.01277 0.00565 -0.1458 0.2159 0.7637
5.500 1.2398 0.01324 0.00605 -0.1450 0.1931 0.7807
5.750 1.2629 0.01365 0.00645 -0.1442 0.1739 0.8026
6.000 1.2854 0.01403 0.00684 -0.1433 0.1565 0.8298
6.250 1.3052 0.01439 0.00722 -0.1418 0.1384 0.8724
6.500 1.3210 0.01474 0.00757 -0.1395 0.1191 1.0000
6.750 1.3428 0.01537 0.00807 -0.1386 0.0979 1.0000
7.000 1.3649 0.01594 0.00858 -0.1378 0.0853 1.0000
7.250 1.3875 0.01645 0.00906 -0.1370 0.0770 1.0000
7.750 1.4313 0.01750 0.01009 -0.1353 0.0630 1.0000
8.000 1.4523 0.01807 0.01064 -0.1343 0.0568 1.0000
8.250 1.4732 0.01861 0.01119 -0.1332 0.0516 1.0000
8.500 1.4930 0.01921 0.01178 -0.1321 0.0473 1.0000
8.750 1.5128 0.01977 0.01239 -0.1309 0.0445 1.0000
9.000 1.5312 0.02039 0.01302 -0.1295 0.0420 1.0000
9.250 1.5471 0.02110 0.01374 -0.1277 0.0394 1.0000
9.500 1.5631 0.02169 0.01439 -0.1258 0.0379 1.0000
9.750 1.5776 0.02235 0.01509 -0.1239 0.0362 1.0000
10.000 1.5908 0.02311 0.01589 -0.1217 0.0346 1.0000
10.250 1.6024 0.02399 0.01680 -0.1195 0.0331 1.0000
10.500 1.6135 0.02492 0.01780 -0.1173 0.0319 1.0000
10.750 1.6266 0.02575 0.01870 -0.1154 0.0311 1.0000
11.000 1.6387 0.02666 0.01970 -0.1135 0.0302 1.0000
11.250 1.6498 0.02768 0.02079 -0.1117 0.0292 1.0000
11.500 1.6597 0.02883 0.02201 -0.1098 0.0282 1.0000
11.750 1.6681 0.03016 0.02340 -0.1079 0.0272 1.0000
12.000 1.6740 0.03175 0.02506 -0.1060 0.0262 1.0000
12.250 1.6845 0.03301 0.02641 -0.1046 0.0255 1.0000
12.500 1.6946 0.03434 0.02784 -0.1033 0.0245 1.0000
12.750 1.7036 0.03582 0.02941 -0.1020 0.0234 1.0000
13.000 1.7113 0.03747 0.03113 -0.1008 0.0224 1.0000
13.250 1.7174 0.03935 0.03307 -0.0996 0.0214 1.0000
13.500 1.7232 0.04132 0.03513 -0.0985 0.0206 1.0000
13.750 1.7301 0.04322 0.03714 -0.0976 0.0195 1.0000
14.000 1.7359 0.04530 0.03930 -0.0968 0.0183 1.0000
14.250 1.7403 0.04761 0.04169 -0.0961 0.0171 1.0000
14.500 1.7433 0.05014 0.04430 -0.0955 0.0161 1.0000
14.750 1.7456 0.05283 0.04709 -0.0950 0.0151 1.0000
15.000 1.7469 0.05574 0.05009 -0.0947 0.0141 1.0000
15.250 1.7466 0.05895 0.05337 -0.0946 0.0132 1.0000
15.500 1.7457 0.06236 0.05690 -0.0946 0.0126 1.0000
15.750 1.7435 0.06605 0.06071 -0.0949 0.0120 1.0000
16.000 1.7405 0.07001 0.06477 -0.0954 0.0114 1.0000
16.250 1.7362 0.07428 0.06916 -0.0961 0.0109 1.0000
16.500 1.7304 0.07892 0.07391 -0.0972 0.0105 1.0000
17.000 1.7164 0.08902 0.08428 -0.1000 0.0099 1.0000
17.250 1.7092 0.09432 0.08972 -0.1018 0.0096 1.0000
17.500 1.7007 0.09995 0.09550 -0.1038 0.0094 1.0000
17.750 1.6914 0.10586 0.10155 -0.1062 0.0091 1.0000
18.000 1.6815 0.11199 0.10782 -0.1088 0.0089 1.0000
18.250 1.6705 0.11843 0.11439 -0.1118 0.0086 1.0000
18.500 1.6588 0.12512 0.12122 -0.1151 0.0085 1.0000
18.750 1.6463 0.13205 0.12829 -0.1187 0.0083 1.0000
19.000 1.6338 0.13909 0.13546 -0.1226 0.0081 1.0000
19.250 1.6203 0.14649 0.14300 -0.1269 0.0080 1.0000
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Polar data table (+)
Polar graphs
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