K3311 (original) (k3311-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: K3311 (original) (k3311-il) Reynolds number: 100,000 Max Cl/Cd: 56.92 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-k3311-il-100000-n5.txt Download as CSV file: xf-k3311-il-100000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3713 0.09781 0.09289 -0.0405 1.0000 0.0698
-9.000 -0.3906 0.09453 0.08976 -0.0450 1.0000 0.0710
-8.750 -0.3923 0.08525 0.08048 -0.0462 1.0000 0.0463
-8.500 -0.3882 0.08276 0.07802 -0.0442 1.0000 0.0448
-8.250 -0.3955 0.07955 0.07491 -0.0439 1.0000 0.0435
-8.000 -0.4106 0.07634 0.07182 -0.0436 1.0000 0.0424
-7.750 -0.4273 0.07217 0.06775 -0.0448 1.0000 0.0413
-7.250 -0.4624 0.05666 0.05172 -0.0533 0.9949 0.0361
-7.000 -0.4419 0.05068 0.04538 -0.0585 0.9862 0.0359
-6.750 -0.4209 0.04494 0.03907 -0.0629 0.9766 0.0369
-6.500 -0.3956 0.04194 0.03600 -0.0654 0.9686 0.0385
-6.250 -0.3678 0.03788 0.03144 -0.0682 0.9611 0.0388
-6.000 -0.3407 0.03435 0.02737 -0.0698 0.9522 0.0389
-5.750 -0.3112 0.03170 0.02430 -0.0713 0.9444 0.0397
-5.500 -0.2788 0.02968 0.02190 -0.0731 0.9371 0.0418
-5.250 -0.2475 0.02759 0.01939 -0.0742 0.9294 0.0428
-5.000 -0.2149 0.02566 0.01707 -0.0752 0.9221 0.0433
-4.750 -0.1838 0.02410 0.01521 -0.0758 0.9141 0.0438
-4.500 -0.1509 0.02274 0.01358 -0.0767 0.9068 0.0445
-4.250 -0.1200 0.02179 0.01241 -0.0772 0.8984 0.0464
-4.000 -0.0879 0.02059 0.01116 -0.0780 0.8912 0.0480
-3.750 -0.0595 0.01968 0.01021 -0.0781 0.8818 0.0489
-3.500 -0.0274 0.01885 0.00932 -0.0789 0.8747 0.0502
-3.250 -0.0010 0.01826 0.00867 -0.0785 0.8640 0.0516
-3.000 0.0277 0.01772 0.00803 -0.0786 0.8548 0.0535
-2.750 0.0571 0.01726 0.00742 -0.0787 0.8459 0.0559
-2.500 0.0837 0.01688 0.00695 -0.0784 0.8352 0.0596
-2.250 0.1119 0.01648 0.00652 -0.0784 0.8258 0.0694
-2.000 0.1395 0.01596 0.00608 -0.0782 0.8162 0.0962
-1.750 0.1616 0.01473 0.00581 -0.0777 0.8059 0.3294
-1.500 0.1843 0.01395 0.00587 -0.0766 0.7969 0.5671
-1.250 0.2091 0.01365 0.00580 -0.0754 0.7875 0.6580
-1.000 0.2333 0.01341 0.00576 -0.0739 0.7777 0.7411
-0.750 0.2647 0.01314 0.00564 -0.0736 0.7697 0.8300
-0.500 0.3415 0.01287 0.00541 -0.0829 0.7608 0.9791
-0.250 0.3773 0.01292 0.00526 -0.0847 0.7510 1.0000
0.000 0.4019 0.01299 0.00515 -0.0841 0.7413 1.0000
0.250 0.4250 0.01310 0.00513 -0.0833 0.7299 1.0000
0.500 0.4491 0.01321 0.00510 -0.0825 0.7190 1.0000
0.750 0.4739 0.01331 0.00507 -0.0819 0.7082 1.0000
1.000 0.4991 0.01342 0.00503 -0.0812 0.6974 1.0000
1.250 0.5236 0.01355 0.00507 -0.0806 0.6863 1.0000
1.500 0.5488 0.01370 0.00513 -0.0800 0.6763 1.0000
1.750 0.5752 0.01385 0.00515 -0.0796 0.6677 1.0000
2.000 0.5997 0.01404 0.00530 -0.0789 0.6574 1.0000
2.250 0.6249 0.01423 0.00545 -0.0784 0.6480 1.0000
2.500 0.6508 0.01442 0.00557 -0.0780 0.6392 1.0000
2.750 0.6749 0.01463 0.00579 -0.0773 0.6286 1.0000
3.000 0.6996 0.01483 0.00600 -0.0767 0.6189 1.0000
3.250 0.7251 0.01501 0.00615 -0.0762 0.6096 1.0000
3.500 0.7490 0.01520 0.00637 -0.0754 0.5983 1.0000
3.750 0.7733 0.01539 0.00657 -0.0747 0.5872 1.0000
4.000 0.7980 0.01557 0.00676 -0.0740 0.5762 1.0000
4.250 0.8230 0.01575 0.00692 -0.0734 0.5659 1.0000
4.500 0.8469 0.01598 0.00720 -0.0727 0.5545 1.0000
4.750 0.8713 0.01622 0.00750 -0.0720 0.5437 1.0000
5.000 0.8959 0.01646 0.00776 -0.0713 0.5334 1.0000
5.250 0.9200 0.01672 0.00806 -0.0706 0.5222 1.0000
5.500 0.9434 0.01701 0.00843 -0.0698 0.5104 1.0000
5.750 0.9667 0.01730 0.00881 -0.0689 0.4979 1.0000
6.000 0.9894 0.01759 0.00915 -0.0679 0.4835 1.0000
6.250 1.0109 0.01787 0.00946 -0.0667 0.4659 1.0000
6.500 1.0318 0.01816 0.00978 -0.0654 0.4475 1.0000
6.750 1.0527 0.01850 0.01021 -0.0642 0.4301 1.0000
7.000 1.0735 0.01886 0.01068 -0.0630 0.4136 1.0000
7.250 1.0938 0.01924 0.01117 -0.0617 0.3963 1.0000
7.500 1.1139 0.01965 0.01168 -0.0604 0.3797 1.0000
7.750 1.1318 0.02012 0.01220 -0.0587 0.3592 1.0000
8.000 1.1440 0.02075 0.01271 -0.0562 0.3233 1.0000
8.250 1.1514 0.02166 0.01336 -0.0532 0.2756 1.0000
8.500 1.1570 0.02276 0.01419 -0.0501 0.2274 1.0000
8.750 1.1636 0.02390 0.01515 -0.0473 0.1882 1.0000
9.000 1.1662 0.02520 0.01624 -0.0440 0.1473 1.0000
9.250 1.1653 0.02676 0.01756 -0.0404 0.1114 1.0000
9.500 1.1645 0.02847 0.01909 -0.0371 0.0807 1.0000
9.750 1.1623 0.03038 0.02085 -0.0340 0.0549 1.0000
10.000 1.1602 0.03237 0.02275 -0.0312 0.0438 1.0000
10.250 1.1604 0.03429 0.02474 -0.0289 0.0382 1.0000
10.500 1.1600 0.03636 0.02689 -0.0269 0.0347 1.0000
10.750 1.1562 0.03882 0.02941 -0.0250 0.0325 1.0000
11.000 1.1570 0.04101 0.03178 -0.0236 0.0311 1.0000
11.250 1.1566 0.04342 0.03436 -0.0224 0.0294 1.0000
11.500 1.1561 0.04595 0.03702 -0.0214 0.0280 1.0000
11.750 1.1552 0.04861 0.03979 -0.0207 0.0267 1.0000
12.000 1.1516 0.05166 0.04292 -0.0202 0.0255 1.0000
12.250 1.1507 0.05452 0.04591 -0.0197 0.0244 1.0000
12.500 1.1528 0.05713 0.04869 -0.0192 0.0237 1.0000
12.750 1.1552 0.05979 0.05149 -0.0186 0.0229 1.0000
13.000 1.1587 0.06239 0.05423 -0.0181 0.0223 1.0000
13.250 1.1625 0.06503 0.05700 -0.0177 0.0217 1.0000
13.500 1.1659 0.06781 0.05992 -0.0174 0.0210 1.0000
13.750 1.1677 0.07081 0.06303 -0.0174 0.0203 1.0000
14.000 1.1692 0.07389 0.06622 -0.0175 0.0197 1.0000
14.250 1.1709 0.07705 0.06945 -0.0175 0.0191 1.0000
14.500 1.1695 0.08081 0.07338 -0.0180 0.0185 1.0000
14.750 1.1653 0.08502 0.07785 -0.0190 0.0181 1.0000
15.000 1.1607 0.08945 0.08251 -0.0202 0.0180 1.0000
15.250 1.1533 0.09444 0.08778 -0.0219 0.0178 1.0000
15.500 1.1445 0.09977 0.09333 -0.0240 0.0177 1.0000
15.750 1.1337 0.10565 0.09945 -0.0266 0.0176 1.0000
16.000 1.1214 0.11204 0.10606 -0.0298 0.0176 1.0000
16.250 1.1068 0.11919 0.11343 -0.0337 0.0175 1.0000
16.500 1.0922 0.12666 0.12110 -0.0380 0.0176 1.0000
16.750 1.0749 0.13519 0.12980 -0.0433 0.0177 1.0000
17.000 1.0582 0.14412 0.13889 -0.0489 0.0178 1.0000
17.250 1.0394 0.15424 0.14915 -0.0553 0.0180 1.0000
17.500 1.0205 0.16521 0.16021 -0.0622 0.0183 1.0000
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Polar data table (+)
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