FX 63-110 AIRFOIL (fx63110-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
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Airfoil: FX 63-110 AIRFOIL (fx63110-il) Reynolds number: 1,000,000 Max Cl/Cd: 136.26 at α=2.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx63110-il-1000000.txt Download as CSV file: xf-fx63110-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.250 -0.7328 0.06629 0.06424 -0.0638 1.0000 0.0118
-13.000 -0.7792 0.05419 0.05197 -0.0712 1.0000 0.0116
-12.750 -0.8036 0.04733 0.04501 -0.0753 1.0000 0.0115
-12.500 -0.8336 0.04122 0.03880 -0.0781 1.0000 0.0115
-12.250 -0.8663 0.03513 0.03256 -0.0816 1.0000 0.0114
-12.000 -0.8494 0.02648 0.02339 -0.0988 0.9976 0.0118
-11.750 -0.8159 0.02395 0.02068 -0.1044 0.9958 0.0122
-11.500 -0.7811 0.02258 0.01920 -0.1081 0.9945 0.0125
-11.250 -0.7479 0.02156 0.01809 -0.1107 0.9929 0.0128
-11.000 -0.7149 0.02050 0.01692 -0.1132 0.9907 0.0133
-10.750 -0.6810 0.01939 0.01567 -0.1158 0.9888 0.0137
-10.500 -0.6463 0.01845 0.01459 -0.1183 0.9872 0.0141
-10.250 -0.6110 0.01723 0.01320 -0.1212 0.9858 0.0146
-10.000 -0.5750 0.01613 0.01202 -0.1240 0.9847 0.0153
-9.750 -0.5416 0.01567 0.01153 -0.1256 0.9826 0.0159
-9.500 -0.5104 0.01519 0.01101 -0.1266 0.9787 0.0165
-9.250 -0.4761 0.01471 0.01045 -0.1283 0.9763 0.0172
-9.000 -0.4406 0.01437 0.01003 -0.1301 0.9743 0.0178
-8.750 -0.4043 0.01332 0.00892 -0.1327 0.9727 0.0189
-8.500 -0.3764 0.01298 0.00856 -0.1328 0.9656 0.0196
-8.250 -0.3426 0.01260 0.00813 -0.1342 0.9616 0.0205
-8.000 -0.3104 0.01224 0.00771 -0.1352 0.9551 0.0213
-7.750 -0.2741 0.01151 0.00690 -0.1373 0.9491 0.0224
-7.500 -0.2348 0.01110 0.00649 -0.1400 0.9441 0.0235
-7.250 -0.1962 0.01085 0.00619 -0.1423 0.9358 0.0248
-7.000 -0.1572 0.01055 0.00582 -0.1447 0.9259 0.0259
-6.750 -0.1210 0.01001 0.00516 -0.1467 0.9129 0.0270
-6.500 -0.0890 0.00963 0.00471 -0.1477 0.8992 0.0284
-6.250 -0.0594 0.00947 0.00448 -0.1481 0.8867 0.0297
-6.000 -0.0307 0.00928 0.00422 -0.1482 0.8754 0.0309
-5.750 -0.0020 0.00914 0.00400 -0.1484 0.8651 0.0317
-5.500 0.0271 0.00871 0.00348 -0.1488 0.8548 0.0334
-5.250 0.0559 0.00847 0.00320 -0.1490 0.8444 0.0349
-5.000 0.0843 0.00832 0.00297 -0.1491 0.8335 0.0363
-4.750 0.1127 0.00820 0.00278 -0.1491 0.8223 0.0378
-4.500 0.1415 0.00804 0.00257 -0.1492 0.8125 0.0390
-4.250 0.1708 0.00780 0.00226 -0.1495 0.8041 0.0418
-4.000 0.1999 0.00765 0.00210 -0.1497 0.7956 0.0445
-3.750 0.2287 0.00756 0.00195 -0.1498 0.7876 0.0472
-3.500 0.2581 0.00738 0.00178 -0.1501 0.7794 0.0545
-3.250 0.2873 0.00724 0.00165 -0.1503 0.7716 0.0708
-3.000 0.3166 0.00709 0.00157 -0.1506 0.7636 0.0916
-2.750 0.3455 0.00701 0.00149 -0.1507 0.7557 0.1079
-2.500 0.3749 0.00688 0.00140 -0.1510 0.7478 0.1293
-2.250 0.4055 0.00649 0.00128 -0.1519 0.7403 0.2316
-2.000 0.4357 0.00623 0.00126 -0.1525 0.7322 0.3208
-1.750 0.4645 0.00619 0.00125 -0.1526 0.7244 0.3539
-1.500 0.4937 0.00614 0.00124 -0.1528 0.7167 0.3786
-1.250 0.5224 0.00613 0.00123 -0.1529 0.7088 0.4020
-1.000 0.5517 0.00605 0.00124 -0.1532 0.7008 0.4342
-0.750 0.5807 0.00598 0.00127 -0.1534 0.6929 0.4839
-0.500 0.6098 0.00595 0.00131 -0.1535 0.6849 0.5208
-0.250 0.6383 0.00599 0.00136 -0.1535 0.6767 0.5496
0.000 0.6669 0.00601 0.00141 -0.1535 0.6682 0.5704
0.250 0.6950 0.00608 0.00145 -0.1535 0.6576 0.5836
0.500 0.7229 0.00616 0.00149 -0.1533 0.6445 0.5956
0.750 0.7507 0.00625 0.00154 -0.1532 0.6313 0.6079
1.000 0.7789 0.00630 0.00160 -0.1531 0.6196 0.6185
1.250 0.8069 0.00638 0.00166 -0.1530 0.6087 0.6290
1.500 0.8346 0.00648 0.00173 -0.1528 0.5972 0.6380
1.750 0.8625 0.00656 0.00180 -0.1527 0.5850 0.6449
2.000 0.8900 0.00668 0.00188 -0.1525 0.5686 0.6521
2.250 0.9171 0.00683 0.00197 -0.1523 0.5492 0.6587
2.500 0.9444 0.00696 0.00206 -0.1521 0.5309 0.6657
2.750 0.9715 0.00713 0.00217 -0.1519 0.5116 0.6727
3.000 0.9978 0.00734 0.00231 -0.1516 0.4884 0.6804
3.250 1.0238 0.00761 0.00247 -0.1512 0.4599 0.6883
3.500 1.0499 0.00786 0.00265 -0.1508 0.4358 0.6962
3.750 1.0763 0.00810 0.00282 -0.1505 0.4152 0.7045
4.000 1.1026 0.00833 0.00301 -0.1502 0.3968 0.7134
4.250 1.1289 0.00857 0.00320 -0.1499 0.3782 0.7231
4.500 1.1547 0.00885 0.00340 -0.1495 0.3526 0.7347
4.750 1.1799 0.00918 0.00365 -0.1490 0.3237 0.7479
5.000 1.2041 0.00961 0.00394 -0.1484 0.2882 0.7617
5.250 1.2277 0.01009 0.00428 -0.1478 0.2517 0.7770
5.500 1.2513 0.01057 0.00464 -0.1471 0.2207 0.7952
5.750 1.2749 0.01099 0.00500 -0.1464 0.1961 0.8166
6.000 1.2985 0.01134 0.00534 -0.1457 0.1756 0.8475
6.250 1.3139 0.01149 0.00560 -0.1430 0.1558 1.0000
6.500 1.3371 0.01205 0.00601 -0.1423 0.1295 1.0000
6.750 1.3589 0.01273 0.00649 -0.1415 0.1000 1.0000
7.000 1.3815 0.01330 0.00695 -0.1407 0.0827 1.0000
7.250 1.4045 0.01382 0.00741 -0.1399 0.0712 1.0000
7.500 1.4272 0.01435 0.00787 -0.1391 0.0602 1.0000
7.750 1.4494 0.01489 0.00835 -0.1383 0.0502 1.0000
8.000 1.4717 0.01541 0.00883 -0.1374 0.0441 1.0000
8.250 1.4942 0.01588 0.00931 -0.1366 0.0406 1.0000
8.500 1.5163 0.01636 0.00979 -0.1357 0.0382 1.0000
8.750 1.5371 0.01695 0.01037 -0.1346 0.0356 1.0000
9.000 1.5580 0.01748 0.01093 -0.1335 0.0341 1.0000
9.250 1.5794 0.01793 0.01143 -0.1326 0.0331 1.0000
9.500 1.5997 0.01844 0.01197 -0.1314 0.0319 1.0000
9.750 1.6185 0.01903 0.01258 -0.1301 0.0306 1.0000
10.000 1.6348 0.01978 0.01335 -0.1283 0.0291 1.0000
10.250 1.6485 0.02051 0.01415 -0.1261 0.0280 1.0000
10.500 1.6649 0.02097 0.01466 -0.1243 0.0273 1.0000
10.750 1.6797 0.02154 0.01528 -0.1223 0.0264 1.0000
11.000 1.6935 0.02218 0.01596 -0.1202 0.0255 1.0000
11.250 1.7055 0.02296 0.01677 -0.1180 0.0246 1.0000
11.500 1.7135 0.02403 0.01788 -0.1153 0.0235 1.0000
11.750 1.7226 0.02506 0.01899 -0.1129 0.0226 1.0000
12.000 1.7370 0.02576 0.01975 -0.1113 0.0219 1.0000
12.250 1.7500 0.02660 0.02063 -0.1096 0.0211 1.0000
12.500 1.7616 0.02755 0.02162 -0.1079 0.0201 1.0000
12.750 1.7697 0.02882 0.02292 -0.1060 0.0192 1.0000
13.000 1.7743 0.03046 0.02463 -0.1039 0.0183 1.0000
13.250 1.7857 0.03158 0.02583 -0.1025 0.0177 1.0000
13.500 1.7956 0.03287 0.02718 -0.1011 0.0169 1.0000
13.750 1.8039 0.03436 0.02872 -0.0998 0.0162 1.0000
14.000 1.8093 0.03618 0.03058 -0.0984 0.0154 1.0000
14.250 1.8094 0.03861 0.03309 -0.0969 0.0147 1.0000
14.500 1.8166 0.04041 0.03497 -0.0959 0.0142 1.0000
14.750 1.8223 0.04241 0.03705 -0.0949 0.0137 1.0000
15.000 1.8263 0.04466 0.03938 -0.0941 0.0132 1.0000
15.250 1.8287 0.04718 0.04197 -0.0934 0.0127 1.0000
15.500 1.8270 0.05029 0.04515 -0.0928 0.0122 1.0000
15.750 1.8203 0.05415 0.04911 -0.0924 0.0117 1.0000
16.000 1.8218 0.05710 0.05217 -0.0923 0.0114 1.0000
16.250 1.8210 0.06046 0.05564 -0.0923 0.0112 1.0000
16.500 1.8189 0.06412 0.05940 -0.0926 0.0109 1.0000
16.750 1.8157 0.06804 0.06344 -0.0931 0.0106 1.0000
17.000 1.8117 0.07223 0.06773 -0.0938 0.0104 1.0000
17.250 1.8057 0.07688 0.07249 -0.0949 0.0102 1.0000
17.500 1.7980 0.08196 0.07768 -0.0962 0.0099 1.0000
17.750 1.7882 0.08752 0.08336 -0.0980 0.0097 1.0000
18.000 1.7741 0.09406 0.09002 -0.1003 0.0095 1.0000
18.250 1.7581 0.10114 0.09725 -0.1031 0.0094 1.0000
18.500 1.7409 0.10861 0.10486 -0.1064 0.0092 1.0000
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