SG6043 (sg6043-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: SG6043 (sg6043-il) Reynolds number: 100,000 Max Cl/Cd: 66.47 at α=7° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sg6043-il-100000.txt Download as CSV file: xf-sg6043-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: SG6043
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
------ -------- --------- --------- -------- -------- --------
-6.750 -0.3860 0.11161 0.10743 -0.0154 1.0000 0.0725
-6.500 -0.4026 0.11086 0.10675 -0.0137 1.0000 0.0735
-6.250 -0.4194 0.11012 0.10609 -0.0134 1.0000 0.0743
-6.000 -0.4301 0.10894 0.10496 -0.0205 1.0000 0.0751
-5.750 -0.4149 0.10346 0.09950 -0.0238 0.9961 0.0762
-5.500 -0.3961 0.09947 0.09550 -0.0201 0.9919 0.0783
-5.250 -0.3750 0.09595 0.09196 -0.0236 0.9865 0.0815
-5.000 -0.3551 0.09215 0.08815 -0.0305 0.9796 0.0859
-4.750 -0.3162 0.08561 0.08149 -0.0501 0.9721 0.0905
-4.500 -0.3071 0.08285 0.07878 -0.0462 0.9669 0.0925
-4.250 -0.2814 0.07954 0.07544 -0.0495 0.9621 0.0973
-4.000 -0.2364 0.07318 0.06884 -0.0665 0.9546 0.1061
-3.750 -0.1823 0.07002 0.06527 -0.0792 0.9490 0.1205
-3.500 -0.1776 0.06581 0.06130 -0.0757 0.9435 0.1228
-3.250 -0.1481 0.06326 0.05874 -0.0780 0.9387 0.1334
-3.000 -0.1173 0.05960 0.05498 -0.0827 0.9328 0.1428
-2.750 -0.0771 0.05616 0.05138 -0.0890 0.9274 0.1588
-2.500 -0.0318 0.05313 0.04821 -0.0950 0.9238 0.1781
-2.250 0.0857 0.04268 0.03568 -0.1152 0.9234 0.0896
-2.000 0.1136 0.03964 0.03253 -0.1167 0.9169 0.0866
-1.750 0.1613 0.03669 0.02896 -0.1207 0.9131 0.0797
-1.500 0.2114 0.03470 0.02630 -0.1243 0.9100 0.0779
-1.250 0.2401 0.03380 0.02523 -0.1248 0.9031 0.0802
-1.000 0.2774 0.03316 0.02435 -0.1264 0.8977 0.0881
-0.750 0.3232 0.03204 0.02321 -0.1294 0.8944 0.1015
-0.500 0.3460 0.03150 0.02279 -0.1289 0.8860 0.1255
-0.250 0.3864 0.03077 0.02236 -0.1313 0.8812 0.1950
0.000 0.4236 0.02853 0.02233 -0.1321 0.8789 0.7828
0.250 0.4364 0.02854 0.02228 -0.1292 0.8679 1.0000
0.500 0.4814 0.02871 0.02210 -0.1321 0.8636 1.0000
0.750 0.5013 0.02920 0.02242 -0.1312 0.8530 1.0000
1.000 0.5456 0.02927 0.02226 -0.1339 0.8484 1.0000
1.250 0.5659 0.02978 0.02265 -0.1330 0.8378 1.0000
1.500 0.6098 0.02973 0.02245 -0.1355 0.8331 1.0000
1.750 0.6305 0.03024 0.02287 -0.1346 0.8223 1.0000
2.000 0.6750 0.03004 0.02257 -0.1371 0.8175 1.0000
2.250 0.6960 0.03051 0.02298 -0.1361 0.8064 1.0000
2.500 0.7418 0.03010 0.02250 -0.1386 0.8018 1.0000
2.750 0.7636 0.03050 0.02287 -0.1376 0.7905 1.0000
3.000 0.8106 0.02985 0.02220 -0.1400 0.7861 1.0000
3.250 0.8332 0.03015 0.02249 -0.1391 0.7747 1.0000
3.500 0.8825 0.02916 0.02150 -0.1415 0.7707 1.0000
3.750 0.9364 0.02785 0.02022 -0.1445 0.7678 1.0000
4.000 0.9603 0.02782 0.02022 -0.1434 0.7557 1.0000
4.250 1.0219 0.02611 0.01855 -0.1476 0.7530 1.0000
4.500 1.0452 0.02599 0.01850 -0.1461 0.7401 1.0000
4.750 1.0805 0.02536 0.01792 -0.1464 0.7296 1.0000
5.000 1.1385 0.02372 0.01636 -0.1501 0.7228 1.0000
5.250 1.1700 0.02315 0.01584 -0.1497 0.7092 1.0000
5.500 1.2050 0.02244 0.01519 -0.1498 0.6951 1.0000
5.750 1.2401 0.02174 0.01456 -0.1500 0.6794 1.0000
6.000 1.2744 0.02111 0.01394 -0.1500 0.6615 1.0000
6.250 1.3053 0.02069 0.01352 -0.1496 0.6412 1.0000
6.500 1.3260 0.02066 0.01353 -0.1476 0.6174 1.0000
6.750 1.3508 0.02058 0.01342 -0.1463 0.5920 1.0000
7.000 1.3732 0.02066 0.01341 -0.1446 0.5637 1.0000
7.250 1.3899 0.02097 0.01364 -0.1421 0.5326 1.0000
7.500 1.4035 0.02144 0.01402 -0.1391 0.4993 1.0000
7.750 1.4137 0.02205 0.01451 -0.1357 0.4645 1.0000
8.000 1.4211 0.02281 0.01510 -0.1319 0.4297 1.0000
8.250 1.4269 0.02372 0.01583 -0.1279 0.3950 1.0000
8.500 1.4316 0.02480 0.01671 -0.1240 0.3616 1.0000
8.750 1.4357 0.02600 0.01772 -0.1203 0.3301 1.0000
9.000 1.4400 0.02730 0.01885 -0.1167 0.3011 1.0000
9.250 1.4455 0.02869 0.02007 -0.1135 0.2752 1.0000
9.500 1.4516 0.03012 0.02136 -0.1105 0.2521 1.0000
9.750 1.4597 0.03162 0.02271 -0.1080 0.2317 1.0000
10.000 1.4685 0.03309 0.02414 -0.1056 0.2135 1.0000
10.250 1.4787 0.03461 0.02560 -0.1035 0.1975 1.0000
10.500 1.4904 0.03615 0.02710 -0.1016 0.1834 1.0000
10.750 1.5035 0.03772 0.02863 -0.1000 0.1707 1.0000
11.000 1.5193 0.03932 0.03012 -0.0988 0.1588 1.0000
11.250 1.5297 0.04089 0.03184 -0.0968 0.1489 1.0000
11.500 1.5446 0.04264 0.03366 -0.0955 0.1395 1.0000
11.750 1.5661 0.04438 0.03529 -0.0951 0.1303 1.0000
12.000 1.5733 0.04618 0.03736 -0.0929 0.1235 1.0000
12.250 1.5952 0.04810 0.03922 -0.0926 0.1160 1.0000
12.500 1.6006 0.05008 0.04149 -0.0903 0.1105 1.0000
12.750 1.6261 0.05218 0.04349 -0.0905 0.1037 1.0000
13.000 1.6247 0.05447 0.04617 -0.0877 0.0999 1.0000
13.250 1.6311 0.05660 0.04845 -0.0859 0.0956 1.0000
13.500 1.6489 0.05926 0.05114 -0.0855 0.0908 1.0000
13.750 1.6411 0.06216 0.05444 -0.0826 0.0882 1.0000
14.000 1.6388 0.06500 0.05755 -0.0805 0.0853 1.0000
14.250 1.6467 0.06733 0.05992 -0.0794 0.0819 1.0000
14.500 1.6491 0.07113 0.06392 -0.0781 0.0792 1.0000
14.750 1.6297 0.07518 0.06837 -0.0757 0.0782 1.0000
15.000 1.6098 0.07970 0.07328 -0.0740 0.0772 1.0000
15.250 1.5888 0.08465 0.07857 -0.0728 0.0763 1.0000
15.500 1.5658 0.09008 0.08433 -0.0724 0.0756 1.0000
15.750 1.5399 0.09616 0.09073 -0.0728 0.0752 1.0000
16.000 1.5094 0.10326 0.09814 -0.0743 0.0752 1.0000
16.250 1.4737 0.11179 0.10696 -0.0774 0.0757 1.0000
16.500 1.4326 0.12222 0.11767 -0.0826 0.0767 1.0000
16.750 1.3888 0.13459 0.13025 -0.0899 0.0780 1.0000
17.000 1.3454 0.14878 0.14458 -0.0992 0.0793 1.0000
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Polar data table (+)
Polar graphs
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