FX 63-110 AIRFOIL (fx63110-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 63-110 AIRFOIL (fx63110-il) Reynolds number: 50,000 Max Cl/Cd: 42.55 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx63110-il-50000-n5.txt Download as CSV file: xf-fx63110-il-50000-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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.3202 0.11530 0.10801 -0.0384 1.0000 0.1174
-9.500 -0.3287 0.10896 0.10169 -0.0421 1.0000 0.0777
-9.000 -0.3493 0.10063 0.09359 -0.0458 1.0000 0.0672
-8.750 -0.3464 0.09774 0.09077 -0.0447 1.0000 0.0665
-8.500 -0.3527 0.09483 0.08798 -0.0444 1.0000 0.0665
-8.250 -0.3605 0.09220 0.08546 -0.0435 1.0000 0.0663
-8.000 -0.3724 0.08980 0.08318 -0.0421 1.0000 0.0662
-7.750 -0.3877 0.08748 0.08100 -0.0406 1.0000 0.0662
-7.500 -0.3990 0.08480 0.07845 -0.0399 1.0000 0.0660
-7.250 -0.4108 0.08154 0.07528 -0.0404 1.0000 0.0659
-7.000 -0.4201 0.07766 0.07148 -0.0422 1.0000 0.0657
-6.750 -0.4262 0.07267 0.06651 -0.0461 1.0000 0.0655
-6.500 -0.4227 0.06662 0.06036 -0.0526 0.9982 0.0653
-6.250 -0.3934 0.05796 0.05127 -0.0660 0.9907 0.0652
-6.000 -0.3509 0.04886 0.04113 -0.0812 0.9847 0.0673
-5.750 -0.3206 0.04603 0.03826 -0.0845 0.9790 0.0703
-5.500 -0.2811 0.04204 0.03375 -0.0906 0.9742 0.0723
-5.250 -0.2412 0.03881 0.02993 -0.0957 0.9689 0.0764
-5.000 -0.1956 0.03582 0.02606 -0.1012 0.9650 0.0806
-4.750 -0.1630 0.03378 0.02386 -0.1032 0.9589 0.0831
-4.500 -0.1252 0.03231 0.02216 -0.1060 0.9540 0.0884
-4.250 -0.0904 0.03103 0.02043 -0.1078 0.9477 0.0943
-4.000 -0.0560 0.02974 0.01906 -0.1093 0.9423 0.0986
-3.750 -0.0228 0.02880 0.01801 -0.1105 0.9364 0.1048
-3.500 0.0094 0.02800 0.01711 -0.1116 0.9298 0.1145
-3.250 0.0477 0.02716 0.01617 -0.1138 0.9251 0.1268
-3.000 0.0790 0.02643 0.01546 -0.1151 0.9174 0.1424
-2.750 0.1214 0.02544 0.01466 -0.1187 0.9124 0.1807
-2.500 0.1652 0.02429 0.01444 -0.1230 0.9077 0.3451
-2.250 0.1948 0.02422 0.01479 -0.1231 0.8995 0.4693
-2.000 0.2306 0.02442 0.01503 -0.1237 0.8940 0.5443
-1.750 0.2541 0.02474 0.01535 -0.1224 0.8840 0.5955
-1.250 0.3078 0.02510 0.01569 -0.1202 0.8677 0.6804
-1.000 0.3419 0.02498 0.01550 -0.1205 0.8620 0.7087
-0.750 0.3662 0.02505 0.01548 -0.1198 0.8515 0.7293
-0.500 0.4019 0.02484 0.01518 -0.1207 0.8457 0.7497
-0.250 0.4243 0.02493 0.01522 -0.1197 0.8349 0.7699
0.000 0.4595 0.02470 0.01492 -0.1204 0.8292 0.7921
0.250 0.4788 0.02480 0.01502 -0.1188 0.8180 0.8134
0.500 0.5064 0.02466 0.01487 -0.1183 0.8104 0.8379
1.000 0.5509 0.02451 0.01477 -0.1157 0.7914 0.9008
1.250 0.5866 0.02426 0.01452 -0.1169 0.7832 1.0000
1.500 0.6204 0.02461 0.01479 -0.1188 0.7728 1.0000
1.750 0.6632 0.02460 0.01469 -0.1215 0.7662 1.0000
2.000 0.6930 0.02501 0.01507 -0.1224 0.7547 1.0000
2.250 0.7278 0.02521 0.01523 -0.1238 0.7456 1.0000
2.500 0.7625 0.02537 0.01535 -0.1250 0.7363 1.0000
2.750 0.7913 0.02574 0.01574 -0.1254 0.7249 1.0000
3.000 0.8263 0.02582 0.01581 -0.1264 0.7159 1.0000
3.250 0.8567 0.02607 0.01609 -0.1267 0.7049 1.0000
3.500 0.8841 0.02642 0.01649 -0.1267 0.6926 1.0000
3.750 0.9144 0.02662 0.01671 -0.1269 0.6813 1.0000
4.000 0.9498 0.02648 0.01662 -0.1274 0.6709 1.0000
4.250 0.9770 0.02666 0.01685 -0.1270 0.6563 1.0000
4.500 1.0044 0.02679 0.01704 -0.1265 0.6413 1.0000
4.750 1.0315 0.02694 0.01727 -0.1259 0.6261 1.0000
5.000 1.0582 0.02712 0.01753 -0.1253 0.6108 1.0000
5.250 1.0845 0.02734 0.01782 -0.1247 0.5954 1.0000
5.500 1.1105 0.02757 0.01816 -0.1240 0.5796 1.0000
5.750 1.1362 0.02781 0.01849 -0.1232 0.5633 1.0000
6.000 1.1618 0.02804 0.01881 -0.1224 0.5465 1.0000
6.250 1.1855 0.02836 0.01925 -0.1214 0.5283 1.0000
6.500 1.2060 0.02876 0.01975 -0.1199 0.5065 1.0000
6.750 1.2281 0.02893 0.01989 -0.1183 0.4815 1.0000
7.000 1.2467 0.02930 0.02023 -0.1164 0.4534 1.0000
7.250 1.2628 0.02990 0.02084 -0.1143 0.4243 1.0000
7.500 1.2783 0.03065 0.02160 -0.1123 0.3968 1.0000
7.750 1.2923 0.03153 0.02246 -0.1102 0.3692 1.0000
8.000 1.3035 0.03254 0.02346 -0.1079 0.3404 1.0000
8.250 1.3118 0.03372 0.02458 -0.1053 0.3115 1.0000
8.500 1.3162 0.03509 0.02585 -0.1024 0.2822 1.0000
8.750 1.3190 0.03673 0.02740 -0.0997 0.2539 1.0000
9.000 1.3212 0.03859 0.02916 -0.0971 0.2281 1.0000
9.250 1.3222 0.04070 0.03111 -0.0948 0.2060 1.0000
9.500 1.3248 0.04289 0.03329 -0.0929 0.1857 1.0000
9.750 1.3275 0.04520 0.03558 -0.0912 0.1690 1.0000
10.000 1.3309 0.04758 0.03795 -0.0897 0.1548 1.0000
10.250 1.3350 0.05000 0.04038 -0.0883 0.1430 1.0000
10.500 1.3396 0.05243 0.04282 -0.0871 0.1340 1.0000
10.750 1.3480 0.05474 0.04527 -0.0860 0.1248 1.0000
11.000 1.3556 0.05710 0.04767 -0.0849 0.1177 1.0000
11.250 1.3635 0.05949 0.05018 -0.0840 0.1107 1.0000
11.500 1.3729 0.06184 0.05260 -0.0831 0.1049 1.0000
11.750 1.3844 0.06419 0.05516 -0.0822 0.0997 1.0000
12.000 1.3986 0.06627 0.05724 -0.0813 0.0955 1.0000
12.250 1.4088 0.06902 0.06029 -0.0805 0.0916 1.0000
12.500 1.4134 0.07216 0.06372 -0.0800 0.0878 1.0000
12.750 1.4200 0.07501 0.06669 -0.0795 0.0845 1.0000
13.000 1.4348 0.07751 0.06920 -0.0788 0.0814 1.0000
13.250 1.4278 0.08211 0.07423 -0.0788 0.0796 1.0000
13.500 1.4176 0.08714 0.07964 -0.0793 0.0779 1.0000
13.750 1.4055 0.09251 0.08533 -0.0804 0.0762 1.0000
14.000 1.3923 0.09819 0.09129 -0.0819 0.0747 1.0000
14.250 1.3784 0.10417 0.09750 -0.0840 0.0734 1.0000
14.500 1.3639 0.11049 0.10404 -0.0866 0.0723 1.0000
14.750 1.3483 0.11737 0.11112 -0.0899 0.0714 1.0000
15.000 1.3501 0.12139 0.11515 -0.0910 0.0695 1.0000
15.250 1.3208 0.13162 0.12563 -0.0974 0.0696 1.0000
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