FX 63-110 AIRFOIL (fx63110-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 63-110 AIRFOIL (fx63110-il) Reynolds number: 100,000 Max Cl/Cd: 64.93 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx63110-il-100000.txt Download as CSV file: xf-fx63110-il-100000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3261 0.10631 0.10125 -0.0387 1.0000 0.1069
-9.000 -0.3500 0.10557 0.10067 -0.0415 1.0000 0.1090
-8.750 -0.3788 0.10491 0.10021 -0.0424 1.0000 0.1095
-8.500 -0.3336 0.09791 0.09309 -0.0381 1.0000 0.1131
-8.250 -0.3296 0.09564 0.09087 -0.0363 1.0000 0.1164
-8.000 -0.3379 0.09389 0.08922 -0.0350 1.0000 0.1206
-7.750 -0.3609 0.09301 0.08848 -0.0330 1.0000 0.1231
-7.500 -0.3932 0.09290 0.08854 -0.0297 1.0000 0.1240
-7.250 -0.4283 0.09219 0.08799 -0.0301 1.0000 0.1249
-7.000 -0.4494 0.08842 0.08434 -0.0349 1.0000 0.1259
-6.750 -0.4211 0.08723 0.08310 -0.0215 1.0000 0.1304
-6.500 -0.4281 0.08567 0.08161 -0.0197 1.0000 0.1344
-6.000 -0.4516 0.07849 0.07457 -0.0281 1.0000 0.1435
-5.750 -0.4269 0.07642 0.07247 -0.0271 0.9957 0.1515
-5.500 -0.3984 0.07091 0.06692 -0.0366 0.9886 0.1633
-5.250 -0.3674 0.06613 0.06207 -0.0449 0.9822 0.1793
-5.000 -0.2499 0.03742 0.03058 -0.0936 0.9817 0.0948
-4.750 -0.2052 0.03380 0.02642 -0.0986 0.9776 0.0950
-4.500 -0.1598 0.03068 0.02291 -0.1033 0.9742 0.0965
-4.250 -0.1182 0.02874 0.02072 -0.1067 0.9697 0.0991
-4.000 -0.0779 0.02743 0.01914 -0.1096 0.9640 0.1044
-3.750 -0.0318 0.02617 0.01748 -0.1130 0.9600 0.1082
-3.500 0.0029 0.02488 0.01620 -0.1148 0.9534 0.1151
-3.250 0.0452 0.02403 0.01521 -0.1175 0.9481 0.1240
-3.000 0.0829 0.02304 0.01437 -0.1196 0.9421 0.1365
-2.750 0.1237 0.02210 0.01358 -0.1222 0.9357 0.1596
-2.500 0.1780 0.02030 0.01287 -0.1282 0.9324 0.3322
-2.250 0.2094 0.02024 0.01344 -0.1285 0.9233 0.5198
-2.000 0.2504 0.02058 0.01377 -0.1300 0.9175 0.5851
-1.750 0.2759 0.02091 0.01410 -0.1291 0.9074 0.6194
-1.500 0.3166 0.02097 0.01414 -0.1305 0.9022 0.6556
-1.250 0.3372 0.02125 0.01448 -0.1285 0.8920 0.6817
-1.000 0.3766 0.02111 0.01435 -0.1296 0.8870 0.7108
-0.750 0.4000 0.02127 0.01451 -0.1284 0.8772 0.7368
-0.500 0.4376 0.02099 0.01423 -0.1291 0.8720 0.7642
-0.250 0.4613 0.02099 0.01425 -0.1279 0.8628 0.7873
0.000 0.4965 0.02066 0.01390 -0.1285 0.8564 0.8106
0.250 0.5214 0.02057 0.01381 -0.1275 0.8474 0.8321
0.500 0.5515 0.02024 0.01348 -0.1271 0.8402 0.8553
0.750 0.5719 0.02016 0.01343 -0.1252 0.8304 0.8788
1.000 0.6006 0.01974 0.01301 -0.1244 0.8233 0.9056
1.250 0.6179 0.01961 0.01294 -0.1221 0.8124 0.9407
1.500 0.6676 0.01909 0.01240 -0.1257 0.8062 1.0000
1.750 0.7049 0.01930 0.01258 -0.1282 0.7949 1.0000
2.000 0.7543 0.01895 0.01216 -0.1317 0.7889 1.0000
2.250 0.7878 0.01918 0.01240 -0.1332 0.7763 1.0000
2.500 0.8232 0.01929 0.01249 -0.1347 0.7648 1.0000
2.750 0.8655 0.01900 0.01215 -0.1367 0.7566 1.0000
3.000 0.8980 0.01896 0.01209 -0.1372 0.7425 1.0000
3.250 0.9299 0.01887 0.01198 -0.1375 0.7279 1.0000
3.500 0.9610 0.01884 0.01194 -0.1376 0.7135 1.0000
3.750 0.9913 0.01887 0.01197 -0.1376 0.6996 1.0000
4.000 1.0214 0.01892 0.01201 -0.1376 0.6858 1.0000
4.250 1.0513 0.01897 0.01205 -0.1375 0.6720 1.0000
4.500 1.0808 0.01902 0.01212 -0.1373 0.6578 1.0000
4.750 1.1097 0.01910 0.01220 -0.1370 0.6429 1.0000
5.000 1.1369 0.01918 0.01229 -0.1364 0.6260 1.0000
5.250 1.1631 0.01921 0.01235 -0.1355 0.6067 1.0000
5.500 1.1895 0.01914 0.01223 -0.1345 0.5855 1.0000
5.750 1.2143 0.01919 0.01227 -0.1334 0.5632 1.0000
6.000 1.2381 0.01935 0.01246 -0.1323 0.5405 1.0000
6.250 1.2620 0.01954 0.01262 -0.1311 0.5171 1.0000
6.500 1.2837 0.01977 0.01279 -0.1296 0.4891 1.0000
6.750 1.3033 0.02013 0.01308 -0.1278 0.4574 1.0000
7.000 1.3210 0.02064 0.01352 -0.1258 0.4225 1.0000
7.250 1.3375 0.02129 0.01409 -0.1238 0.3862 1.0000
7.500 1.3521 0.02207 0.01474 -0.1215 0.3479 1.0000
7.750 1.3637 0.02304 0.01556 -0.1190 0.3039 1.0000
8.000 1.3716 0.02438 0.01662 -0.1160 0.2582 1.0000
8.250 1.3762 0.02613 0.01804 -0.1128 0.2154 1.0000
8.500 1.3795 0.02809 0.01968 -0.1095 0.1820 1.0000
8.750 1.3846 0.02988 0.02131 -0.1064 0.1571 1.0000
9.000 1.3912 0.03164 0.02292 -0.1037 0.1400 1.0000
9.250 1.4020 0.03340 0.02462 -0.1015 0.1271 1.0000
9.500 1.4163 0.03520 0.02638 -0.0998 0.1170 1.0000
9.750 1.4350 0.03711 0.02814 -0.0989 0.1087 1.0000
10.000 1.4536 0.03880 0.02998 -0.0977 0.1020 1.0000
10.250 1.4841 0.04112 0.03219 -0.0984 0.0956 1.0000
10.500 1.5002 0.04295 0.03428 -0.0970 0.0908 1.0000
10.750 1.5288 0.04523 0.03649 -0.0976 0.0857 1.0000
11.000 1.5498 0.04805 0.03956 -0.0971 0.0818 1.0000
11.250 1.5606 0.05036 0.04218 -0.0952 0.0786 1.0000
11.500 1.5725 0.05270 0.04471 -0.0936 0.0755 1.0000
11.750 1.5995 0.05693 0.04895 -0.0948 0.0716 1.0000
12.000 1.5906 0.05935 0.05180 -0.0907 0.0705 1.0000
12.250 1.5812 0.06231 0.05515 -0.0871 0.0694 1.0000
12.500 1.5699 0.06561 0.05882 -0.0840 0.0682 1.0000
12.750 1.5571 0.06918 0.06272 -0.0815 0.0671 1.0000
13.000 1.5439 0.07302 0.06685 -0.0796 0.0660 1.0000
13.250 1.5300 0.07719 0.07129 -0.0783 0.0651 1.0000
13.500 1.5203 0.08129 0.07559 -0.0775 0.0639 1.0000
13.750 1.4999 0.08658 0.08117 -0.0774 0.0637 1.0000
14.000 1.4635 0.09375 0.08872 -0.0786 0.0643 1.0000
14.250 1.4159 0.10339 0.09877 -0.0822 0.0658 1.0000
14.500 1.3708 0.11423 0.10993 -0.0879 0.0675 1.0000
14.750 1.3296 0.12605 0.12198 -0.0952 0.0693 1.0000
15.000 1.2945 0.13851 0.13455 -0.1033 0.0707 1.0000
15.250 1.2685 0.15060 0.14671 -0.1109 0.0717 1.0000
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