K3311 (smoothed) (k3311sm-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: K3311 (smoothed) (k3311sm-il) Reynolds number: 100,000 Max Cl/Cd: 57.04 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-k3311sm-il-100000-n5.txt Download as CSV file: xf-k3311sm-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: K3311 (smoothed)
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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3986 0.07796 0.07329 -0.0478 1.0000 0.0314
-8.000 -0.4086 0.07531 0.07074 -0.0468 1.0000 0.0311
-7.750 -0.4199 0.07186 0.06737 -0.0470 1.0000 0.0308
-7.500 -0.4317 0.06863 0.06417 -0.0466 1.0000 0.0305
-7.250 -0.4437 0.06557 0.06113 -0.0456 1.0000 0.0301
-7.000 -0.4286 0.05872 0.05407 -0.0529 0.9912 0.0295
-6.750 -0.4094 0.05199 0.04701 -0.0594 0.9815 0.0289
-6.500 -0.3886 0.04596 0.04053 -0.0641 0.9721 0.0286
-6.250 -0.3671 0.04090 0.03496 -0.0669 0.9624 0.0285
-6.000 -0.3396 0.03643 0.02990 -0.0696 0.9554 0.0289
-5.750 -0.3136 0.03305 0.02590 -0.0707 0.9464 0.0303
-5.500 -0.2831 0.03012 0.02231 -0.0722 0.9397 0.0322
-5.250 -0.2539 0.02793 0.01986 -0.0732 0.9320 0.0335
-5.000 -0.2201 0.02597 0.01756 -0.0747 0.9264 0.0349
-4.750 -0.1908 0.02445 0.01578 -0.0751 0.9176 0.0369
-4.500 -0.1567 0.02322 0.01419 -0.0762 0.9111 0.0407
-4.250 -0.1274 0.02167 0.01254 -0.0764 0.9025 0.0429
-4.000 -0.0964 0.02054 0.01135 -0.0771 0.8947 0.0459
-3.750 -0.0654 0.01973 0.01041 -0.0776 0.8863 0.0514
-3.500 -0.0377 0.01878 0.00943 -0.0775 0.8767 0.0554
-3.250 -0.0061 0.01800 0.00857 -0.0781 0.8693 0.0621
-3.000 0.0199 0.01738 0.00790 -0.0777 0.8583 0.0717
-2.750 0.0479 0.01676 0.00724 -0.0777 0.8486 0.0858
-2.500 0.0768 0.01594 0.00661 -0.0779 0.8401 0.1305
-2.250 0.0980 0.01469 0.00631 -0.0772 0.8290 0.3559
-2.000 0.1223 0.01412 0.00625 -0.0763 0.8190 0.5202
-1.750 0.1488 0.01377 0.00614 -0.0754 0.8104 0.6252
-1.500 0.1699 0.01344 0.00617 -0.0731 0.7995 0.7360
-1.250 0.1980 0.01318 0.00606 -0.0720 0.7900 0.8231
-1.000 0.2398 0.01302 0.00582 -0.0742 0.7816 0.8784
-0.750 0.2916 0.01293 0.00560 -0.0789 0.7714 0.9319
-0.500 0.3426 0.01287 0.00535 -0.0836 0.7618 0.9824
-0.250 0.3776 0.01290 0.00518 -0.0852 0.7521 1.0000
0.000 0.4003 0.01299 0.00512 -0.0844 0.7407 1.0000
0.250 0.4243 0.01309 0.00507 -0.0836 0.7302 1.0000
0.500 0.4494 0.01319 0.00501 -0.0830 0.7207 1.0000
0.750 0.4737 0.01331 0.00502 -0.0823 0.7101 1.0000
1.000 0.4981 0.01345 0.00506 -0.0817 0.6999 1.0000
1.250 0.5235 0.01357 0.00507 -0.0811 0.6905 1.0000
1.500 0.5484 0.01372 0.00514 -0.0805 0.6804 1.0000
1.750 0.5729 0.01388 0.00524 -0.0798 0.6701 1.0000
2.000 0.5984 0.01404 0.00531 -0.0793 0.6608 1.0000
2.250 0.6234 0.01420 0.00541 -0.0787 0.6507 1.0000
2.500 0.6480 0.01439 0.00558 -0.0780 0.6404 1.0000
2.750 0.6732 0.01456 0.00570 -0.0775 0.6309 1.0000
3.000 0.6983 0.01475 0.00585 -0.0769 0.6209 1.0000
3.250 0.7227 0.01495 0.00605 -0.0762 0.6103 1.0000
3.500 0.7476 0.01515 0.00625 -0.0756 0.6003 1.0000
3.750 0.7729 0.01534 0.00642 -0.0750 0.5905 1.0000
4.000 0.7968 0.01557 0.00667 -0.0743 0.5793 1.0000
4.250 0.8211 0.01579 0.00691 -0.0736 0.5685 1.0000
4.500 0.8457 0.01601 0.00716 -0.0729 0.5578 1.0000
4.750 0.8701 0.01623 0.00739 -0.0722 0.5468 1.0000
5.000 0.8936 0.01648 0.00770 -0.0714 0.5346 1.0000
5.250 0.9171 0.01673 0.00803 -0.0705 0.5226 1.0000
5.500 0.9405 0.01699 0.00834 -0.0697 0.5103 1.0000
5.750 0.9638 0.01726 0.00865 -0.0688 0.4977 1.0000
6.000 0.9866 0.01754 0.00898 -0.0679 0.4844 1.0000
6.250 1.0090 0.01783 0.00935 -0.0669 0.4704 1.0000
6.500 1.0309 0.01814 0.00973 -0.0658 0.4554 1.0000
6.750 1.0522 0.01846 0.01013 -0.0646 0.4396 1.0000
7.000 1.0729 0.01881 0.01055 -0.0633 0.4229 1.0000
7.250 1.0930 0.01919 0.01101 -0.0620 0.4054 1.0000
7.500 1.1120 0.01960 0.01145 -0.0604 0.3866 1.0000
7.750 1.1293 0.02006 0.01196 -0.0587 0.3636 1.0000
8.000 1.1442 0.02060 0.01247 -0.0566 0.3359 1.0000
8.250 1.1567 0.02128 0.01305 -0.0542 0.3039 1.0000
8.500 1.1671 0.02209 0.01376 -0.0517 0.2712 1.0000
8.750 1.1767 0.02299 0.01457 -0.0491 0.2385 1.0000
9.000 1.1839 0.02402 0.01549 -0.0463 0.2059 1.0000
9.250 1.1880 0.02515 0.01650 -0.0431 0.1759 1.0000
9.500 1.1898 0.02647 0.01767 -0.0398 0.1453 1.0000
9.750 1.1905 0.02797 0.01903 -0.0366 0.1161 1.0000
10.000 1.1896 0.02970 0.02062 -0.0336 0.0912 1.0000
10.250 1.1888 0.03153 0.02237 -0.0309 0.0733 1.0000
10.500 1.1878 0.03348 0.02430 -0.0285 0.0618 1.0000
10.750 1.1866 0.03557 0.02643 -0.0264 0.0540 1.0000
11.000 1.1845 0.03783 0.02872 -0.0245 0.0483 1.0000
11.250 1.1839 0.04009 0.03108 -0.0230 0.0442 1.0000
11.500 1.1831 0.04249 0.03361 -0.0217 0.0409 1.0000
11.750 1.1803 0.04518 0.03638 -0.0207 0.0387 1.0000
12.000 1.1762 0.04812 0.03938 -0.0198 0.0369 1.0000
12.250 1.1773 0.05065 0.04210 -0.0191 0.0350 1.0000
12.500 1.1776 0.05335 0.04493 -0.0186 0.0330 1.0000
12.750 1.1770 0.05621 0.04789 -0.0183 0.0311 1.0000
13.000 1.1754 0.05923 0.05099 -0.0181 0.0297 1.0000
13.250 1.1745 0.06223 0.05402 -0.0177 0.0286 1.0000
13.500 1.1784 0.06484 0.05685 -0.0173 0.0277 1.0000
13.750 1.1821 0.06755 0.05974 -0.0168 0.0268 1.0000
14.000 1.1850 0.07043 0.06279 -0.0166 0.0258 1.0000
14.250 1.1857 0.07364 0.06617 -0.0168 0.0248 1.0000
14.500 1.1850 0.07705 0.06971 -0.0173 0.0239 1.0000
14.750 1.1834 0.08063 0.07340 -0.0180 0.0230 1.0000
15.000 1.1827 0.08417 0.07705 -0.0186 0.0224 1.0000
15.250 1.1803 0.08807 0.08102 -0.0193 0.0216 1.0000
15.500 1.1748 0.09269 0.08589 -0.0207 0.0213 1.0000
15.750 1.1672 0.09778 0.09123 -0.0225 0.0211 1.0000
16.000 1.1572 0.10344 0.09714 -0.0249 0.0209 1.0000
16.250 1.1458 0.10954 0.10347 -0.0278 0.0207 1.0000
16.500 1.1322 0.11631 0.11046 -0.0313 0.0206 1.0000
16.750 1.1177 0.12356 0.11793 -0.0353 0.0206 1.0000
17.000 1.1010 0.13164 0.12622 -0.0401 0.0207 1.0000
17.250 1.0826 0.14066 0.13542 -0.0458 0.0207 1.0000
17.500 1.0624 0.15072 0.14564 -0.0522 0.0209 1.0000
17.750 1.0419 0.16164 0.15668 -0.0590 0.0212 1.0000
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Polar data table (+)
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