K3311 (original) (k3311-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: K3311 (original) (k3311-il) Reynolds number: 100,000 Max Cl/Cd: 55.91 at α=8° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-k3311-il-100000.txt Download as CSV file: xf-k3311-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: K3311 (original)
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
------ -------- --------- --------- -------- -------- --------
-10.500 -0.3679 0.11699 0.11179 -0.0318 1.0000 0.0917
-10.250 -0.3798 0.11509 0.10999 -0.0354 1.0000 0.0948
-10.000 -0.3987 0.11356 0.10858 -0.0400 1.0000 0.0956
-9.750 -0.3698 0.10723 0.10219 -0.0355 1.0000 0.0984
-9.500 -0.3597 0.10424 0.09921 -0.0345 1.0000 0.1025
-9.250 -0.3638 0.10159 0.09663 -0.0360 1.0000 0.1076
-9.000 -0.3840 0.09962 0.09481 -0.0398 1.0000 0.1096
-8.750 -0.3717 0.09515 0.09035 -0.0377 1.0000 0.1130
-8.500 -0.3616 0.09252 0.08774 -0.0360 1.0000 0.1186
-8.250 -0.3763 0.09024 0.08559 -0.0375 1.0000 0.1230
-8.000 -0.4064 0.08858 0.08412 -0.0386 1.0000 0.1242
-7.750 -0.4388 0.08584 0.08150 -0.0425 1.0000 0.1248
-7.500 -0.3938 0.08243 0.07806 -0.0335 1.0000 0.1316
-7.250 -0.4092 0.08041 0.07616 -0.0322 1.0000 0.1350
-7.000 -0.4427 0.07797 0.07381 -0.0350 1.0000 0.1386
-6.750 -0.4646 0.07454 0.07041 -0.0359 1.0000 0.1410
-6.500 -0.4536 0.07284 0.06882 -0.0298 1.0000 0.1441
-6.250 -0.4594 0.07088 0.06690 -0.0279 1.0000 0.1490
-6.000 -0.4784 0.06716 0.06308 -0.0312 1.0000 0.1564
-5.750 -0.4739 0.06549 0.06152 -0.0271 1.0000 0.1599
-5.500 -0.4648 0.06177 0.05769 -0.0305 0.9971 0.1728
-5.250 -0.4336 0.05833 0.05419 -0.0341 0.9899 0.1900
-5.000 -0.4014 0.05507 0.05083 -0.0386 0.9827 0.2180
-4.750 -0.3729 0.05219 0.04787 -0.0417 0.9739 0.2470
-4.500 -0.3440 0.04973 0.04539 -0.0433 0.9662 0.2774
-4.250 -0.2730 0.03219 0.02478 -0.0584 0.9601 0.0899
-4.000 -0.2342 0.02967 0.02172 -0.0605 0.9537 0.0872
-3.750 -0.1974 0.02771 0.01921 -0.0619 0.9458 0.0849
-3.500 -0.1557 0.02620 0.01725 -0.0640 0.9397 0.0829
-3.250 -0.1202 0.02486 0.01573 -0.0653 0.9313 0.0830
-3.000 -0.0754 0.02346 0.01428 -0.0682 0.9265 0.0846
-2.750 -0.0449 0.02267 0.01349 -0.0688 0.9166 0.0893
-2.500 0.0016 0.02173 0.01251 -0.0720 0.9122 0.0946
-2.250 0.0289 0.02095 0.01181 -0.0718 0.9016 0.0997
-2.000 0.0759 0.02000 0.01087 -0.0752 0.8973 0.1153
-1.750 0.0975 0.01820 0.01041 -0.0746 0.8868 0.3765
-1.500 0.1267 0.01688 0.01053 -0.0725 0.8824 0.7716
-1.250 0.2481 0.01623 0.01002 -0.0883 0.8847 0.9928
-1.000 0.2777 0.01616 0.00971 -0.0895 0.8731 1.0000
-0.750 0.3091 0.01607 0.00940 -0.0904 0.8633 1.0000
-0.500 0.3424 0.01596 0.00910 -0.0913 0.8539 1.0000
-0.250 0.3659 0.01607 0.00905 -0.0906 0.8417 1.0000
0.000 0.3924 0.01612 0.00896 -0.0902 0.8307 1.0000
0.250 0.4270 0.01596 0.00865 -0.0910 0.8225 1.0000
0.500 0.4497 0.01609 0.00866 -0.0898 0.8099 1.0000
0.750 0.4738 0.01620 0.00868 -0.0889 0.7980 1.0000
1.000 0.5000 0.01628 0.00867 -0.0883 0.7873 1.0000
1.250 0.5303 0.01624 0.00852 -0.0882 0.7787 1.0000
1.500 0.5527 0.01649 0.00871 -0.0871 0.7668 1.0000
1.750 0.5772 0.01671 0.00887 -0.0864 0.7561 1.0000
2.000 0.6076 0.01671 0.00878 -0.0863 0.7481 1.0000
2.250 0.6293 0.01703 0.00910 -0.0852 0.7363 1.0000
2.500 0.6530 0.01731 0.00936 -0.0843 0.7255 1.0000
2.750 0.6808 0.01742 0.00942 -0.0839 0.7164 1.0000
3.000 0.7058 0.01763 0.00961 -0.0832 0.7058 1.0000
3.250 0.7294 0.01789 0.00990 -0.0823 0.6944 1.0000
3.500 0.7550 0.01808 0.01007 -0.0816 0.6836 1.0000
3.750 0.7842 0.01812 0.01006 -0.0813 0.6740 1.0000
4.000 0.8075 0.01841 0.01038 -0.0803 0.6617 1.0000
4.250 0.8308 0.01873 0.01076 -0.0793 0.6496 1.0000
4.500 0.8552 0.01902 0.01109 -0.0785 0.6380 1.0000
4.750 0.8812 0.01923 0.01132 -0.0778 0.6268 1.0000
5.000 0.9076 0.01940 0.01153 -0.0772 0.6154 1.0000
5.250 0.9303 0.01968 0.01189 -0.0761 0.6023 1.0000
5.500 0.9539 0.01992 0.01221 -0.0751 0.5894 1.0000
5.750 0.9782 0.02007 0.01242 -0.0741 0.5757 1.0000
6.000 1.0033 0.02004 0.01243 -0.0731 0.5600 1.0000
6.250 1.0285 0.01999 0.01237 -0.0719 0.5433 1.0000
6.500 1.0532 0.02008 0.01246 -0.0709 0.5271 1.0000
6.750 1.0765 0.02033 0.01278 -0.0698 0.5113 1.0000
7.000 1.0979 0.02064 0.01322 -0.0685 0.4942 1.0000
7.250 1.1191 0.02094 0.01364 -0.0671 0.4767 1.0000
7.500 1.1398 0.02104 0.01377 -0.0654 0.4556 1.0000
7.750 1.1546 0.02090 0.01364 -0.0626 0.4262 1.0000
8.000 1.1663 0.02086 0.01358 -0.0594 0.3929 1.0000
8.250 1.1777 0.02116 0.01391 -0.0565 0.3594 1.0000
8.500 1.1878 0.02171 0.01440 -0.0536 0.3251 1.0000
8.750 1.1944 0.02250 0.01511 -0.0502 0.2844 1.0000
9.000 1.1920 0.02376 0.01609 -0.0458 0.2239 1.0000
9.250 1.1749 0.02597 0.01769 -0.0397 0.1476 1.0000
9.500 1.1556 0.02876 0.01995 -0.0341 0.1027 1.0000
9.750 1.1449 0.03124 0.02221 -0.0300 0.0851 1.0000
10.000 1.1429 0.03331 0.02429 -0.0270 0.0748 1.0000
10.250 1.1425 0.03545 0.02646 -0.0245 0.0686 1.0000
10.500 1.1462 0.03740 0.02843 -0.0224 0.0636 1.0000
10.750 1.1525 0.03950 0.03047 -0.0206 0.0593 1.0000
11.000 1.1641 0.04124 0.03231 -0.0191 0.0552 1.0000
11.250 1.1791 0.04304 0.03408 -0.0179 0.0520 1.0000
11.500 1.2162 0.04548 0.03650 -0.0176 0.0492 1.0000
11.750 1.2390 0.04791 0.03923 -0.0168 0.0477 1.0000
12.000 1.2542 0.05055 0.04214 -0.0158 0.0463 1.0000
12.250 1.2627 0.05316 0.04499 -0.0145 0.0448 1.0000
12.500 1.2696 0.05597 0.04801 -0.0132 0.0436 1.0000
12.750 1.2715 0.05927 0.05160 -0.0118 0.0432 1.0000
13.000 1.2656 0.06292 0.05559 -0.0104 0.0433 1.0000
13.250 1.2529 0.06692 0.05992 -0.0091 0.0436 1.0000
13.500 1.2362 0.07133 0.06466 -0.0085 0.0439 1.0000
13.750 1.2162 0.07619 0.06983 -0.0085 0.0442 1.0000
14.000 1.1937 0.08160 0.07553 -0.0094 0.0447 1.0000
14.250 1.1696 0.08759 0.08179 -0.0112 0.0452 1.0000
14.500 1.1435 0.09430 0.08873 -0.0139 0.0457 1.0000
14.750 1.1161 0.10174 0.09639 -0.0177 0.0463 1.0000
15.000 1.0878 0.11007 0.10489 -0.0225 0.0469 1.0000
15.250 1.0564 0.11998 0.11497 -0.0287 0.0476 1.0000
15.500 1.0283 0.13050 0.12559 -0.0354 0.0484 1.0000
15.750 1.0089 0.14014 0.13526 -0.0410 0.0494 1.0000
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Polar data table (+)
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