NACA 2412 (naca2412-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 2412 (naca2412-il) Reynolds number: 100,000 Max Cl/Cd: 49.35 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca2412-il-100000-n5.txt Download as CSV file: xf-naca2412-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 2412
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
------ -------- --------- --------- -------- -------- --------
-11.250 -0.6947 0.06549 0.05983 -0.0551 1.0000 0.0469
-11.000 -0.7371 0.05730 0.05143 -0.0608 1.0000 0.0464
-10.750 -0.7675 0.05270 0.04658 -0.0599 1.0000 0.0464
-10.500 -0.7873 0.04853 0.04206 -0.0582 1.0000 0.0470
-10.250 -0.7998 0.04479 0.03787 -0.0560 1.0000 0.0478
-10.000 -0.8042 0.04164 0.03428 -0.0535 1.0000 0.0487
-9.750 -0.7941 0.03990 0.03249 -0.0519 1.0000 0.0495
-9.500 -0.7838 0.03826 0.03072 -0.0502 1.0000 0.0504
-9.250 -0.7724 0.03679 0.02909 -0.0485 1.0000 0.0517
-9.000 -0.7610 0.03522 0.02730 -0.0466 1.0000 0.0533
-8.750 -0.7491 0.03350 0.02530 -0.0448 1.0000 0.0549
-8.500 -0.7359 0.03175 0.02321 -0.0429 1.0000 0.0564
-8.250 -0.7208 0.03016 0.02135 -0.0412 1.0000 0.0575
-8.000 -0.7041 0.02902 0.02020 -0.0398 1.0000 0.0590
-7.750 -0.6869 0.02813 0.01927 -0.0384 1.0000 0.0609
-7.500 -0.6693 0.02718 0.01819 -0.0369 1.0000 0.0631
-7.250 -0.6511 0.02614 0.01697 -0.0355 1.0000 0.0653
-7.000 -0.6321 0.02514 0.01576 -0.0341 1.0000 0.0672
-6.750 -0.6136 0.02423 0.01487 -0.0328 1.0000 0.0692
-6.500 -0.5946 0.02355 0.01417 -0.0316 1.0000 0.0721
-6.250 -0.5749 0.02289 0.01343 -0.0304 1.0000 0.0759
-6.000 -0.5550 0.02220 0.01266 -0.0293 1.0000 0.0797
-5.750 -0.5322 0.02157 0.01205 -0.0288 0.9991 0.0841
-5.500 -0.4960 0.02092 0.01127 -0.0308 0.9945 0.0912
-5.250 -0.4610 0.02026 0.01066 -0.0327 0.9891 0.1005
-5.000 -0.4240 0.01967 0.01008 -0.0350 0.9841 0.1125
-4.750 -0.3896 0.01913 0.00956 -0.0367 0.9775 0.1263
-4.500 -0.3518 0.01865 0.00911 -0.0391 0.9723 0.1443
-4.250 -0.3188 0.01821 0.00873 -0.0404 0.9647 0.1654
-4.000 -0.2811 0.01776 0.00841 -0.0427 0.9595 0.1931
-3.750 -0.2496 0.01735 0.00812 -0.0437 0.9513 0.2233
-3.500 -0.2119 0.01696 0.00784 -0.0458 0.9458 0.2607
-3.250 -0.1804 0.01659 0.00759 -0.0467 0.9374 0.2963
-3.000 -0.1445 0.01620 0.00734 -0.0484 0.9310 0.3364
-2.750 -0.1140 0.01584 0.00713 -0.0489 0.9221 0.3775
-2.500 -0.0801 0.01544 0.00692 -0.0501 0.9149 0.4274
-2.250 -0.0513 0.01508 0.00680 -0.0501 0.9051 0.4833
-2.000 -0.0182 0.01470 0.00665 -0.0508 0.8977 0.5496
-1.750 0.0088 0.01440 0.00658 -0.0501 0.8867 0.6154
-1.500 0.0380 0.01410 0.00652 -0.0497 0.8775 0.6859
-1.250 0.0666 0.01386 0.00649 -0.0488 0.8674 0.7551
-1.000 0.0959 0.01374 0.00650 -0.0481 0.8562 0.8154
-0.750 0.1316 0.01365 0.00643 -0.0487 0.8463 0.8651
-0.500 0.1707 0.01359 0.00635 -0.0502 0.8351 0.9047
-0.250 0.2121 0.01356 0.00626 -0.0524 0.8225 0.9361
0.000 0.2557 0.01351 0.00614 -0.0552 0.8097 0.9616
0.250 0.3012 0.01345 0.00599 -0.0585 0.7961 0.9821
0.500 0.3490 0.01337 0.00583 -0.0625 0.7814 0.9979
0.750 0.3761 0.01335 0.00571 -0.0623 0.7651 1.0000
1.000 0.4001 0.01336 0.00563 -0.0614 0.7485 1.0000
1.250 0.4241 0.01340 0.00558 -0.0605 0.7317 1.0000
1.500 0.4482 0.01346 0.00556 -0.0596 0.7147 1.0000
1.750 0.4721 0.01355 0.00556 -0.0587 0.6976 1.0000
2.000 0.4960 0.01365 0.00559 -0.0578 0.6804 1.0000
2.250 0.5200 0.01378 0.00564 -0.0568 0.6632 1.0000
2.500 0.5438 0.01392 0.00571 -0.0559 0.6459 1.0000
2.750 0.5678 0.01408 0.00579 -0.0549 0.6286 1.0000
3.000 0.5917 0.01425 0.00591 -0.0540 0.6114 1.0000
3.250 0.6156 0.01445 0.00604 -0.0531 0.5943 1.0000
3.500 0.6396 0.01466 0.00619 -0.0522 0.5773 1.0000
3.750 0.6635 0.01488 0.00637 -0.0513 0.5604 1.0000
4.000 0.6874 0.01512 0.00657 -0.0504 0.5438 1.0000
4.500 0.7351 0.01565 0.00704 -0.0486 0.5106 1.0000
4.750 0.7586 0.01593 0.00728 -0.0477 0.4926 1.0000
5.000 0.7812 0.01622 0.00754 -0.0466 0.4706 1.0000
5.250 0.8032 0.01653 0.00781 -0.0455 0.4467 1.0000
5.500 0.8252 0.01686 0.00809 -0.0443 0.4228 1.0000
5.750 0.8471 0.01722 0.00841 -0.0432 0.3991 1.0000
6.000 0.8686 0.01760 0.00877 -0.0420 0.3734 1.0000
6.250 0.8891 0.01805 0.00913 -0.0408 0.3448 1.0000
6.500 0.9089 0.01856 0.00954 -0.0394 0.3133 1.0000
6.750 0.9279 0.01916 0.01001 -0.0380 0.2802 1.0000
7.000 0.9461 0.01984 0.01057 -0.0366 0.2472 1.0000
7.250 0.9637 0.02060 0.01120 -0.0351 0.2156 1.0000
7.500 0.9807 0.02143 0.01190 -0.0336 0.1869 1.0000
7.750 0.9968 0.02234 0.01268 -0.0321 0.1614 1.0000
8.000 1.0131 0.02324 0.01353 -0.0305 0.1399 1.0000
8.250 1.0283 0.02421 0.01442 -0.0288 0.1231 1.0000
8.500 1.0431 0.02518 0.01537 -0.0271 0.1107 1.0000
8.750 1.0569 0.02621 0.01638 -0.0253 0.1019 1.0000
9.000 1.0698 0.02726 0.01745 -0.0234 0.0949 1.0000
9.250 1.0821 0.02835 0.01857 -0.0214 0.0893 1.0000
9.500 1.0932 0.02939 0.01967 -0.0193 0.0842 1.0000
9.750 1.1011 0.03066 0.02090 -0.0169 0.0804 1.0000
10.000 1.1133 0.03177 0.02214 -0.0150 0.0768 1.0000
10.250 1.1247 0.03298 0.02346 -0.0132 0.0737 1.0000
10.500 1.1349 0.03428 0.02479 -0.0114 0.0709 1.0000
10.750 1.1443 0.03577 0.02625 -0.0097 0.0684 1.0000
11.000 1.1566 0.03709 0.02776 -0.0083 0.0658 1.0000
11.250 1.1679 0.03852 0.02931 -0.0068 0.0634 1.0000
11.500 1.1781 0.04000 0.03088 -0.0055 0.0613 1.0000
11.750 1.1875 0.04158 0.03249 -0.0042 0.0594 1.0000
12.000 1.1973 0.04332 0.03431 -0.0030 0.0576 1.0000
12.250 1.2052 0.04513 0.03636 -0.0017 0.0557 1.0000
12.500 1.2122 0.04705 0.03846 -0.0006 0.0539 1.0000
12.750 1.2178 0.04902 0.04056 0.0004 0.0522 1.0000
13.000 1.2231 0.05100 0.04261 0.0013 0.0508 1.0000
13.250 1.2303 0.05303 0.04463 0.0021 0.0494 1.0000
13.500 1.2299 0.05579 0.04767 0.0028 0.0482 1.0000
13.750 1.2271 0.05886 0.05102 0.0033 0.0470 1.0000
14.000 1.2231 0.06210 0.05451 0.0034 0.0458 1.0000
14.250 1.2181 0.06550 0.05811 0.0032 0.0447 1.0000
14.500 1.2129 0.06901 0.06179 0.0027 0.0438 1.0000
14.750 1.2084 0.07252 0.06542 0.0021 0.0429 1.0000
15.000 1.2054 0.07594 0.06892 0.0014 0.0421 1.0000
15.250 1.2037 0.07935 0.07236 0.0009 0.0413 1.0000
15.500 1.1838 0.08549 0.07881 -0.0016 0.0410 1.0000
15.750 1.1616 0.09243 0.08604 -0.0050 0.0407 1.0000
16.000 1.1361 0.10046 0.09435 -0.0093 0.0405 1.0000
16.250 1.1064 0.10995 0.10409 -0.0150 0.0405 1.0000
16.500 1.0698 0.12178 0.11617 -0.0224 0.0407 1.0000
16.750 1.0170 0.13908 0.13368 -0.0336 0.0412 1.0000
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