K3311 (smoothed) (k3311sm-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: K3311 (smoothed) (k3311sm-il) Reynolds number: 50,000 Max Cl/Cd: 36.38 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-k3311sm-il-50000-n5.txt Download as CSV file: xf-k3311sm-il-50000-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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.3567 0.11319 0.10605 -0.0338 1.0000 0.1154
-9.500 -0.3579 0.11032 0.10326 -0.0348 1.0000 0.1192
-9.250 -0.3727 0.10232 0.09530 -0.0419 1.0000 0.0655
-9.000 -0.3646 0.09891 0.09193 -0.0408 1.0000 0.0638
-8.750 -0.3646 0.09555 0.08864 -0.0412 1.0000 0.0628
-8.500 -0.3666 0.09221 0.08539 -0.0415 1.0000 0.0615
-8.000 -0.4118 0.08155 0.07501 -0.0500 1.0000 0.0531
-7.750 -0.4174 0.07815 0.07167 -0.0498 1.0000 0.0529
-7.500 -0.4235 0.07490 0.06846 -0.0493 1.0000 0.0527
-7.250 -0.4294 0.07175 0.06534 -0.0485 1.0000 0.0524
-7.000 -0.4368 0.06846 0.06202 -0.0479 1.0000 0.0523
-6.750 -0.4420 0.06529 0.05880 -0.0469 1.0000 0.0521
-6.500 -0.4455 0.06209 0.05552 -0.0460 1.0000 0.0518
-6.250 -0.4471 0.05881 0.05209 -0.0451 1.0000 0.0516
-6.000 -0.4459 0.05553 0.04863 -0.0443 1.0000 0.0513
-5.750 -0.4420 0.05228 0.04513 -0.0435 1.0000 0.0510
-5.500 -0.4168 0.04777 0.04012 -0.0468 0.9934 0.0509
-5.250 -0.3858 0.04356 0.03527 -0.0502 0.9851 0.0514
-5.000 -0.3541 0.04016 0.03112 -0.0527 0.9764 0.0534
-4.750 -0.3220 0.03749 0.02825 -0.0552 0.9692 0.0565
-4.500 -0.2897 0.03504 0.02535 -0.0568 0.9606 0.0583
-4.250 -0.2556 0.03289 0.02273 -0.0583 0.9528 0.0608
-4.000 -0.2199 0.03127 0.02053 -0.0597 0.9448 0.0659
-3.750 -0.1880 0.02958 0.01875 -0.0608 0.9365 0.0701
-3.500 -0.1518 0.02824 0.01721 -0.0621 0.9293 0.0753
-3.250 -0.1210 0.02717 0.01602 -0.0627 0.9201 0.0839
-3.000 -0.0823 0.02614 0.01477 -0.0645 0.9136 0.0943
-2.750 -0.0528 0.02524 0.01385 -0.0652 0.9035 0.1108
-2.500 -0.0173 0.02416 0.01287 -0.0669 0.8960 0.1428
-2.250 0.0110 0.02228 0.01231 -0.0679 0.8874 0.3709
-2.000 0.0331 0.02153 0.01239 -0.0659 0.8783 0.6098
-1.750 0.0594 0.02089 0.01240 -0.0630 0.8712 0.8104
-1.500 0.1596 0.02048 0.01173 -0.0758 0.8705 1.0000
-1.250 0.1845 0.02052 0.01141 -0.0759 0.8585 1.0000
-1.000 0.2121 0.02058 0.01117 -0.0763 0.8475 1.0000
-0.750 0.2462 0.02057 0.01086 -0.0776 0.8392 1.0000
-0.500 0.2716 0.02071 0.01075 -0.0774 0.8276 1.0000
-0.250 0.2978 0.02086 0.01070 -0.0773 0.8166 1.0000
0.000 0.3281 0.02095 0.01058 -0.0778 0.8074 1.0000
0.250 0.3569 0.02108 0.01052 -0.0779 0.7976 1.0000
0.500 0.3819 0.02129 0.01059 -0.0775 0.7865 1.0000
0.750 0.4102 0.02144 0.01060 -0.0776 0.7770 1.0000
1.000 0.4396 0.02156 0.01060 -0.0777 0.7677 1.0000
1.250 0.4635 0.02184 0.01078 -0.0771 0.7566 1.0000
1.500 0.4904 0.02204 0.01089 -0.0768 0.7468 1.0000
1.750 0.5199 0.02217 0.01093 -0.0769 0.7380 1.0000
2.000 0.5430 0.02249 0.01122 -0.0761 0.7268 1.0000
2.250 0.5687 0.02275 0.01143 -0.0757 0.7167 1.0000
2.500 0.5986 0.02287 0.01149 -0.0757 0.7081 1.0000
2.750 0.6209 0.02325 0.01189 -0.0748 0.6967 1.0000
3.000 0.6454 0.02356 0.01219 -0.0742 0.6862 1.0000
3.250 0.6750 0.02368 0.01229 -0.0741 0.6775 1.0000
3.500 0.6978 0.02406 0.01270 -0.0732 0.6661 1.0000
3.750 0.7208 0.02444 0.01314 -0.0724 0.6549 1.0000
4.000 0.7465 0.02471 0.01344 -0.0718 0.6447 1.0000
4.250 0.7741 0.02489 0.01366 -0.0715 0.6349 1.0000
4.500 0.7956 0.02534 0.01418 -0.0704 0.6229 1.0000
4.750 0.8184 0.02573 0.01468 -0.0695 0.6113 1.0000
5.000 0.8432 0.02603 0.01506 -0.0687 0.6003 1.0000
5.250 0.8711 0.02618 0.01526 -0.0683 0.5899 1.0000
5.500 0.8924 0.02661 0.01580 -0.0672 0.5771 1.0000
5.750 0.9139 0.02703 0.01638 -0.0660 0.5644 1.0000
6.000 0.9359 0.02742 0.01689 -0.0649 0.5514 1.0000
6.250 0.9581 0.02779 0.01739 -0.0638 0.5384 1.0000
6.500 0.9804 0.02814 0.01787 -0.0626 0.5250 1.0000
6.750 1.0023 0.02850 0.01839 -0.0614 0.5111 1.0000
7.000 1.0236 0.02886 0.01890 -0.0601 0.4966 1.0000
7.250 1.0441 0.02924 0.01943 -0.0587 0.4814 1.0000
7.500 1.0638 0.02962 0.01996 -0.0571 0.4655 1.0000
7.750 1.0832 0.02999 0.02051 -0.0555 0.4488 1.0000
8.000 1.1026 0.03031 0.02096 -0.0538 0.4315 1.0000
8.250 1.1185 0.03079 0.02157 -0.0518 0.4127 1.0000
8.500 1.1315 0.03137 0.02230 -0.0494 0.3924 1.0000
8.750 1.1451 0.03180 0.02279 -0.0470 0.3708 1.0000
9.000 1.1518 0.03253 0.02364 -0.0439 0.3464 1.0000
9.250 1.1551 0.03335 0.02448 -0.0406 0.3202 1.0000
9.500 1.1546 0.03437 0.02545 -0.0369 0.2935 1.0000
9.750 1.1524 0.03568 0.02670 -0.0335 0.2661 1.0000
10.000 1.1492 0.03733 0.02828 -0.0306 0.2390 1.0000
10.250 1.1447 0.03932 0.03020 -0.0281 0.2123 1.0000
10.500 1.1387 0.04170 0.03246 -0.0260 0.1865 1.0000
10.750 1.1321 0.04443 0.03513 -0.0244 0.1620 1.0000
11.000 1.1249 0.04748 0.03808 -0.0231 0.1402 1.0000
11.250 1.1175 0.05078 0.04128 -0.0223 0.1227 1.0000
11.500 1.1105 0.05423 0.04466 -0.0216 0.1086 1.0000
11.750 1.1050 0.05769 0.04812 -0.0212 0.0967 1.0000
12.000 1.1012 0.06111 0.05154 -0.0208 0.0871 1.0000
12.250 1.0979 0.06449 0.05487 -0.0206 0.0806 1.0000
12.500 1.0976 0.06771 0.05823 -0.0203 0.0734 1.0000
12.750 1.0962 0.07103 0.06153 -0.0202 0.0682 1.0000
13.000 1.0988 0.07410 0.06481 -0.0199 0.0633 1.0000
13.250 1.1011 0.07712 0.06787 -0.0197 0.0597 1.0000
13.500 1.1047 0.08017 0.07104 -0.0194 0.0564 1.0000
13.750 1.1049 0.08388 0.07505 -0.0198 0.0531 1.0000
14.000 1.1048 0.08757 0.07890 -0.0203 0.0505 1.0000
14.250 1.1076 0.09087 0.08229 -0.0204 0.0485 1.0000
14.500 1.1128 0.09413 0.08563 -0.0203 0.0469 1.0000
14.750 1.1045 0.09959 0.09148 -0.0221 0.0462 1.0000
15.000 1.0931 0.10570 0.09788 -0.0246 0.0457 1.0000
15.250 1.0789 0.11258 0.10502 -0.0279 0.0454 1.0000
15.500 1.0620 0.12038 0.11302 -0.0320 0.0453 1.0000
15.750 1.0430 0.12915 0.12199 -0.0370 0.0455 1.0000
16.000 1.0220 0.13911 0.13211 -0.0430 0.0458 1.0000
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