FX 63-110 AIRFOIL (fx63110-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 63-110 AIRFOIL (fx63110-il) Reynolds number: 100,000 Max Cl/Cd: 66.06 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx63110-il-100000-n5.txt Download as CSV file: xf-fx63110-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3438 0.09287 0.08787 -0.0442 1.0000 0.0376
-8.750 -0.3504 0.08969 0.08478 -0.0440 1.0000 0.0375
-8.500 -0.3606 0.08668 0.08187 -0.0433 1.0000 0.0374
-8.250 -0.3742 0.08420 0.07950 -0.0418 1.0000 0.0371
-8.000 -0.3931 0.08213 0.07755 -0.0394 0.9999 0.0370
-7.750 -0.3839 0.07466 0.07010 -0.0492 0.9898 0.0378
-7.500 -0.3698 0.06141 0.05676 -0.0690 0.9769 0.0383
-7.250 -0.3504 0.04774 0.04246 -0.0911 0.9639 0.0390
-7.000 -0.3209 0.03997 0.03388 -0.1018 0.9553 0.0400
-6.750 -0.2892 0.03538 0.02885 -0.1077 0.9494 0.0421
-6.500 -0.2566 0.03348 0.02676 -0.1108 0.9436 0.0447
-6.250 -0.2176 0.03058 0.02340 -0.1153 0.9401 0.0469
-6.000 -0.1842 0.02836 0.02074 -0.1179 0.9337 0.0501
-5.750 -0.1461 0.02625 0.01808 -0.1209 0.9293 0.0531
-5.500 -0.1071 0.02440 0.01586 -0.1236 0.9262 0.0550
-5.250 -0.0750 0.02331 0.01475 -0.1251 0.9203 0.0583
-5.000 -0.0400 0.02229 0.01359 -0.1268 0.9153 0.0617
-4.750 -0.0021 0.02119 0.01231 -0.1288 0.9118 0.0647
-4.500 0.0325 0.02031 0.01132 -0.1302 0.9068 0.0684
-4.250 0.0654 0.01965 0.01071 -0.1314 0.9005 0.0735
-4.000 0.1025 0.01895 0.00991 -0.1332 0.8962 0.0791
-3.750 0.1380 0.01826 0.00923 -0.1349 0.8910 0.0856
-3.500 0.1716 0.01775 0.00868 -0.1362 0.8841 0.0971
-3.250 0.2103 0.01709 0.00804 -0.1386 0.8796 0.1161
-3.000 0.2447 0.01650 0.00753 -0.1402 0.8727 0.1448
-2.750 0.2818 0.01552 0.00723 -0.1429 0.8663 0.2896
-2.500 0.3184 0.01514 0.00711 -0.1447 0.8604 0.4072
-2.250 0.3476 0.01502 0.00715 -0.1447 0.8507 0.4623
-2.000 0.3800 0.01496 0.00715 -0.1451 0.8431 0.5102
-1.750 0.4091 0.01502 0.00721 -0.1449 0.8336 0.5509
-1.500 0.4393 0.01505 0.00721 -0.1450 0.8256 0.5800
-1.250 0.4682 0.01509 0.00722 -0.1448 0.8170 0.6050
-1.000 0.4969 0.01513 0.00724 -0.1446 0.8089 0.6289
-0.750 0.5253 0.01516 0.00724 -0.1443 0.8005 0.6494
-0.500 0.5533 0.01520 0.00725 -0.1440 0.7922 0.6654
-0.250 0.5821 0.01522 0.00723 -0.1439 0.7839 0.6805
0.000 0.6090 0.01527 0.00727 -0.1434 0.7751 0.6947
0.250 0.6375 0.01528 0.00725 -0.1432 0.7671 0.7087
0.500 0.6636 0.01535 0.00733 -0.1426 0.7577 0.7224
0.750 0.6924 0.01536 0.00730 -0.1424 0.7500 0.7364
1.000 0.7177 0.01545 0.00742 -0.1418 0.7399 0.7504
1.250 0.7452 0.01548 0.00745 -0.1414 0.7313 0.7644
1.500 0.7712 0.01554 0.00753 -0.1408 0.7216 0.7787
1.750 0.7969 0.01560 0.00762 -0.1401 0.7118 0.7935
2.000 0.8235 0.01560 0.00764 -0.1394 0.7030 0.8090
2.250 0.8470 0.01567 0.00778 -0.1383 0.6918 0.8259
2.500 0.8708 0.01569 0.00784 -0.1372 0.6816 0.8450
2.750 0.8943 0.01566 0.00786 -0.1359 0.6715 0.8690
3.000 0.9142 0.01561 0.00789 -0.1339 0.6583 0.9082
3.250 0.9410 0.01559 0.00787 -0.1335 0.6428 1.0000
3.500 0.9703 0.01574 0.00799 -0.1337 0.6264 1.0000
3.750 0.9989 0.01594 0.00815 -0.1339 0.6109 1.0000
4.000 1.0270 0.01616 0.00836 -0.1339 0.5959 1.0000
4.250 1.0545 0.01641 0.00861 -0.1338 0.5807 1.0000
4.500 1.0816 0.01666 0.00887 -0.1336 0.5653 1.0000
4.750 1.1082 0.01694 0.00915 -0.1333 0.5492 1.0000
5.000 1.1341 0.01723 0.00943 -0.1329 0.5313 1.0000
5.250 1.1587 0.01754 0.00973 -0.1322 0.5101 1.0000
5.500 1.1825 0.01790 0.01003 -0.1314 0.4862 1.0000
5.750 1.2051 0.01833 0.01037 -0.1304 0.4594 1.0000
6.000 1.2273 0.01883 0.01080 -0.1294 0.4340 1.0000
6.250 1.2493 0.01936 0.01129 -0.1284 0.4098 1.0000
6.500 1.2703 0.01995 0.01183 -0.1273 0.3841 1.0000
6.750 1.2895 0.02062 0.01242 -0.1260 0.3527 1.0000
7.000 1.3065 0.02142 0.01309 -0.1244 0.3150 1.0000
7.250 1.3218 0.02236 0.01383 -0.1226 0.2756 1.0000
7.500 1.3359 0.02341 0.01469 -0.1207 0.2407 1.0000
7.750 1.3500 0.02449 0.01565 -0.1189 0.2129 1.0000
8.000 1.3636 0.02561 0.01667 -0.1170 0.1892 1.0000
8.250 1.3765 0.02674 0.01778 -0.1151 0.1667 1.0000
8.500 1.3867 0.02796 0.01893 -0.1129 0.1467 1.0000
8.750 1.3962 0.02920 0.02014 -0.1105 0.1288 1.0000
9.000 1.4042 0.03055 0.02146 -0.1081 0.1146 1.0000
9.250 1.4110 0.03201 0.02290 -0.1057 0.1042 1.0000
9.500 1.4169 0.03358 0.02447 -0.1033 0.0962 1.0000
9.750 1.4233 0.03519 0.02618 -0.1011 0.0902 1.0000
10.000 1.4286 0.03695 0.02800 -0.0990 0.0852 1.0000
10.250 1.4315 0.03898 0.03004 -0.0970 0.0814 1.0000
10.500 1.4390 0.04076 0.03197 -0.0953 0.0774 1.0000
10.750 1.4449 0.04271 0.03403 -0.0938 0.0738 1.0000
11.000 1.4488 0.04492 0.03626 -0.0923 0.0708 1.0000
11.250 1.4550 0.04706 0.03850 -0.0910 0.0683 1.0000
11.500 1.4634 0.04907 0.04071 -0.0898 0.0658 1.0000
11.750 1.4708 0.05121 0.04298 -0.0887 0.0633 1.0000
12.000 1.4770 0.05346 0.04533 -0.0878 0.0610 1.0000
12.250 1.4822 0.05589 0.04780 -0.0869 0.0589 1.0000
12.500 1.4891 0.05829 0.05035 -0.0860 0.0569 1.0000
12.750 1.4951 0.06079 0.05309 -0.0853 0.0548 1.0000
13.000 1.4988 0.06347 0.05596 -0.0848 0.0526 1.0000
13.250 1.5012 0.06629 0.05891 -0.0844 0.0507 1.0000
13.500 1.5033 0.06921 0.06190 -0.0842 0.0491 1.0000
13.750 1.5056 0.07232 0.06515 -0.0839 0.0475 1.0000
14.000 1.5036 0.07599 0.06914 -0.0840 0.0458 1.0000
14.250 1.5012 0.07979 0.07318 -0.0843 0.0442 1.0000
14.500 1.4985 0.08367 0.07725 -0.0849 0.0428 1.0000
14.750 1.4954 0.08762 0.08134 -0.0857 0.0415 1.0000
15.000 1.4931 0.09148 0.08527 -0.0866 0.0402 1.0000
15.250 1.4904 0.09564 0.08953 -0.0876 0.0391 1.0000
15.500 1.4797 0.10140 0.09563 -0.0897 0.0382 1.0000
15.750 1.4680 0.10752 0.10206 -0.0922 0.0372 1.0000
16.000 1.4557 0.11393 0.10873 -0.0953 0.0364 1.0000
16.250 1.4428 0.12071 0.11576 -0.0989 0.0356 1.0000
16.500 1.4293 0.12787 0.12313 -0.1030 0.0350 1.0000
16.750 1.4151 0.13546 0.13093 -0.1077 0.0344 1.0000
17.000 1.3992 0.14375 0.13942 -0.1132 0.0340 1.0000
17.250 1.3682 0.15669 0.15265 -0.1223 0.0342 1.0000
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