NACA 4412 (naca4412-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 4412 (naca4412-il) Reynolds number: 200,000 Max Cl/Cd: 76.56 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca4412-il-200000-n5.txt Download as CSV file: xf-naca4412-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 4412
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.7160 0.04811 0.04402 -0.0746 1.0000 0.0293
-10.750 -0.7336 0.04319 0.03880 -0.0759 0.9982 0.0295
-10.500 -0.7076 0.04197 0.03758 -0.0781 0.9951 0.0302
-10.250 -0.6856 0.03969 0.03514 -0.0809 0.9911 0.0309
-10.000 -0.6657 0.03649 0.03160 -0.0840 0.9866 0.0319
-9.750 -0.6446 0.03320 0.02786 -0.0867 0.9826 0.0330
-9.500 -0.6240 0.03032 0.02442 -0.0883 0.9775 0.0343
-9.250 -0.5962 0.02846 0.02232 -0.0901 0.9744 0.0354
-9.000 -0.5668 0.02740 0.02119 -0.0915 0.9714 0.0363
-8.750 -0.5409 0.02632 0.01995 -0.0921 0.9665 0.0373
-8.500 -0.5106 0.02511 0.01852 -0.0935 0.9632 0.0387
-8.250 -0.4782 0.02379 0.01689 -0.0952 0.9608 0.0401
-8.000 -0.4514 0.02265 0.01549 -0.0956 0.9558 0.0411
-7.750 -0.4219 0.02166 0.01446 -0.0965 0.9516 0.0422
-7.500 -0.3883 0.02093 0.01367 -0.0981 0.9485 0.0436
-7.250 -0.3536 0.02013 0.01274 -0.0997 0.9459 0.0453
-7.000 -0.3286 0.01939 0.01188 -0.0993 0.9383 0.0466
-6.750 -0.2966 0.01861 0.01093 -0.1003 0.9339 0.0479
-6.500 -0.2632 0.01782 0.01011 -0.1016 0.9306 0.0496
-6.250 -0.2384 0.01736 0.00962 -0.1011 0.9226 0.0515
-6.000 -0.2073 0.01682 0.00901 -0.1018 0.9177 0.0539
-5.750 -0.1765 0.01627 0.00836 -0.1023 0.9128 0.0562
-5.500 -0.1501 0.01575 0.00784 -0.1021 0.9050 0.0587
-5.250 -0.1188 0.01529 0.00733 -0.1028 0.8999 0.0621
-5.000 -0.0916 0.01493 0.00691 -0.1026 0.8919 0.0664
-4.750 -0.0619 0.01450 0.00649 -0.1029 0.8853 0.0719
-4.500 -0.0336 0.01417 0.00610 -0.1029 0.8776 0.0780
-4.250 -0.0045 0.01380 0.00574 -0.1031 0.8698 0.0852
-4.000 0.0237 0.01350 0.00542 -0.1030 0.8614 0.0930
-3.750 0.0529 0.01323 0.00511 -0.1032 0.8532 0.1028
-3.500 0.0806 0.01297 0.00488 -0.1031 0.8437 0.1135
-3.250 0.1100 0.01271 0.00461 -0.1032 0.8353 0.1263
-3.000 0.1373 0.01250 0.00442 -0.1030 0.8245 0.1416
-2.750 0.1654 0.01228 0.00423 -0.1030 0.8147 0.1604
-2.250 0.2212 0.01191 0.00393 -0.1028 0.7930 0.2036
-2.000 0.2491 0.01178 0.00380 -0.1027 0.7821 0.2278
-1.750 0.2771 0.01164 0.00367 -0.1026 0.7710 0.2516
-1.500 0.3043 0.01152 0.00358 -0.1023 0.7588 0.2753
-1.250 0.3316 0.01140 0.00349 -0.1021 0.7470 0.3027
-1.000 0.3589 0.01128 0.00342 -0.1019 0.7353 0.3368
-0.750 0.3858 0.01113 0.00336 -0.1017 0.7232 0.3814
-0.500 0.4118 0.01090 0.00335 -0.1013 0.7108 0.4524
-0.250 0.4358 0.01053 0.00340 -0.1005 0.6989 0.5870
0.000 0.4578 0.01019 0.00347 -0.0988 0.6873 0.7261
0.250 0.4817 0.00995 0.00353 -0.0971 0.6753 0.8695
0.500 0.5278 0.00992 0.00349 -0.1006 0.6623 0.9867
0.750 0.5572 0.01003 0.00348 -0.1009 0.6503 1.0000
1.000 0.5831 0.01016 0.00349 -0.1004 0.6386 1.0000
1.250 0.6090 0.01030 0.00353 -0.0999 0.6266 1.0000
1.500 0.6350 0.01044 0.00359 -0.0995 0.6151 1.0000
1.750 0.6609 0.01060 0.00365 -0.0991 0.6042 1.0000
2.000 0.6869 0.01076 0.00373 -0.0986 0.5932 1.0000
2.250 0.7129 0.01092 0.00383 -0.0982 0.5825 1.0000
2.500 0.7388 0.01110 0.00394 -0.0978 0.5724 1.0000
2.750 0.7648 0.01128 0.00407 -0.0974 0.5621 1.0000
3.000 0.7907 0.01147 0.00420 -0.0970 0.5521 1.0000
3.500 0.8423 0.01186 0.00452 -0.0962 0.5323 1.0000
3.750 0.8679 0.01207 0.00469 -0.0957 0.5229 1.0000
4.000 0.8935 0.01229 0.00488 -0.0953 0.5132 1.0000
4.250 0.9192 0.01250 0.00508 -0.0949 0.5042 1.0000
4.500 0.9445 0.01273 0.00529 -0.0944 0.4952 1.0000
4.750 0.9700 0.01294 0.00553 -0.0940 0.4861 1.0000
5.000 0.9948 0.01320 0.00575 -0.0934 0.4761 1.0000
5.250 1.0189 0.01344 0.00598 -0.0927 0.4628 1.0000
5.500 1.0425 0.01369 0.00623 -0.0919 0.4485 1.0000
5.750 1.0664 0.01395 0.00649 -0.0912 0.4356 1.0000
6.000 1.0894 0.01423 0.00675 -0.0903 0.4207 1.0000
6.250 1.1109 0.01456 0.00704 -0.0892 0.4008 1.0000
6.500 1.1315 0.01493 0.00734 -0.0880 0.3793 1.0000
6.750 1.1527 0.01529 0.00767 -0.0869 0.3593 1.0000
7.000 1.1730 0.01571 0.00804 -0.0856 0.3385 1.0000
7.250 1.1921 0.01619 0.00846 -0.0842 0.3165 1.0000
7.500 1.2102 0.01672 0.00892 -0.0827 0.2916 1.0000
7.750 1.2268 0.01733 0.00944 -0.0809 0.2660 1.0000
8.000 1.2415 0.01805 0.01004 -0.0789 0.2389 1.0000
8.250 1.2540 0.01886 0.01073 -0.0766 0.2107 1.0000
8.500 1.2642 0.01972 0.01146 -0.0740 0.1830 1.0000
8.750 1.2736 0.02068 0.01230 -0.0713 0.1563 1.0000
9.000 1.2828 0.02170 0.01321 -0.0688 0.1345 1.0000
9.250 1.2926 0.02272 0.01417 -0.0664 0.1178 1.0000
9.500 1.3024 0.02375 0.01518 -0.0641 0.1049 1.0000
9.750 1.3118 0.02483 0.01625 -0.0619 0.0942 1.0000
10.250 1.3302 0.02712 0.01857 -0.0578 0.0779 1.0000
10.500 1.3377 0.02844 0.01991 -0.0558 0.0725 1.0000
10.750 1.3466 0.02969 0.02123 -0.0540 0.0682 1.0000
11.000 1.3529 0.03118 0.02276 -0.0521 0.0645 1.0000
11.250 1.3592 0.03274 0.02437 -0.0504 0.0616 1.0000
11.500 1.3666 0.03426 0.02599 -0.0489 0.0588 1.0000
11.750 1.3720 0.03599 0.02779 -0.0475 0.0563 1.0000
12.000 1.3747 0.03803 0.02988 -0.0460 0.0541 1.0000
12.250 1.3792 0.03997 0.03191 -0.0448 0.0523 1.0000
12.500 1.3848 0.04187 0.03393 -0.0438 0.0503 1.0000
12.750 1.3891 0.04394 0.03610 -0.0428 0.0485 1.0000
13.000 1.3914 0.04627 0.03850 -0.0420 0.0469 1.0000
13.250 1.3909 0.04894 0.04122 -0.0412 0.0455 1.0000
13.500 1.3933 0.05138 0.04377 -0.0405 0.0442 1.0000
13.750 1.3970 0.05376 0.04629 -0.0400 0.0427 1.0000
14.000 1.3994 0.05631 0.04895 -0.0397 0.0412 1.0000
14.250 1.4008 0.05906 0.05179 -0.0394 0.0399 1.0000
14.500 1.4003 0.06208 0.05488 -0.0393 0.0388 1.0000
14.750 1.3978 0.06537 0.05821 -0.0393 0.0378 1.0000
15.000 1.4002 0.06817 0.06117 -0.0393 0.0366 1.0000
15.250 1.4011 0.07118 0.06432 -0.0394 0.0353 1.0000
15.500 1.4010 0.07439 0.06765 -0.0397 0.0342 1.0000
15.750 1.4000 0.07778 0.07114 -0.0402 0.0332 1.0000
16.000 1.3976 0.08139 0.07482 -0.0408 0.0323 1.0000
16.250 1.3945 0.08508 0.07857 -0.0414 0.0315 1.0000
16.500 1.3937 0.08857 0.08223 -0.0420 0.0305 1.0000
16.750 1.3919 0.09227 0.08608 -0.0428 0.0295 1.0000
17.000 1.3894 0.09613 0.09006 -0.0438 0.0285 1.0000
17.250 1.3862 0.10013 0.09415 -0.0449 0.0278 1.0000
17.500 1.3824 0.10425 0.09835 -0.0462 0.0271 1.0000
17.750 1.3780 0.10844 0.10259 -0.0476 0.0265 1.0000
18.000 1.3744 0.11267 0.10702 -0.0490 0.0257 1.0000
18.250 1.3702 0.11707 0.11158 -0.0507 0.0249 1.0000
18.500 1.3656 0.12160 0.11625 -0.0525 0.0242 1.0000
18.750 1.3608 0.12622 0.12099 -0.0546 0.0235 1.0000
19.000 1.3559 0.13091 0.12577 -0.0568 0.0230 1.0000
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Polar data table (+)
Polar graphs
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