N-22 (n22-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: N-22 (n22-il) Reynolds number: 100,000 Max Cl/Cd: 54.14 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-n22-il-100000-n5.txt Download as CSV file: xf-n22-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: N-22
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 -0.3702 0.09205 0.08684 -0.0446 0.9999 0.0536
-11.000 -0.3773 0.08848 0.08334 -0.0451 0.9999 0.0533
-10.750 -0.3892 0.08509 0.08004 -0.0451 0.9999 0.0531
-10.500 -0.4078 0.08205 0.07711 -0.0441 0.9999 0.0531
-10.250 -0.4331 0.07950 0.07468 -0.0421 0.9999 0.0529
-10.000 -0.4507 0.07442 0.06966 -0.0451 0.9977 0.0530
-9.750 -0.4511 0.05877 0.05365 -0.0639 0.9853 0.0536
-9.500 -0.4460 0.04778 0.04199 -0.0733 0.9751 0.0539
-9.250 -0.4304 0.04070 0.03410 -0.0781 0.9670 0.0545
-9.000 -0.4042 0.03711 0.03008 -0.0808 0.9610 0.0557
-8.750 -0.3740 0.03553 0.02839 -0.0826 0.9556 0.0571
-8.500 -0.3453 0.03363 0.02623 -0.0840 0.9489 0.0586
-8.250 -0.3122 0.03118 0.02336 -0.0863 0.9447 0.0599
-8.000 -0.2854 0.02923 0.02102 -0.0869 0.9370 0.0611
-7.750 -0.2535 0.02743 0.01883 -0.0882 0.9313 0.0627
-7.500 -0.2203 0.02598 0.01697 -0.0894 0.9262 0.0649
-7.250 -0.1928 0.02500 0.01599 -0.0896 0.9179 0.0668
-7.000 -0.1589 0.02403 0.01491 -0.0909 0.9129 0.0689
-6.750 -0.1311 0.02316 0.01390 -0.0908 0.9045 0.0710
-6.500 -0.0989 0.02224 0.01281 -0.0915 0.8983 0.0736
-6.250 -0.0696 0.02147 0.01195 -0.0916 0.8907 0.0768
-6.000 -0.0397 0.02089 0.01139 -0.0920 0.8832 0.0809
-5.750 -0.0100 0.02030 0.01071 -0.0921 0.8757 0.0858
-5.500 0.0189 0.01967 0.01007 -0.0921 0.8675 0.0905
-5.250 0.0478 0.01920 0.00958 -0.0921 0.8593 0.0977
-5.000 0.0766 0.01871 0.00910 -0.0920 0.8508 0.1071
-4.750 0.1043 0.01828 0.00866 -0.0918 0.8415 0.1190
-4.500 0.1339 0.01782 0.00823 -0.0918 0.8332 0.1356
-4.250 0.1604 0.01748 0.00794 -0.0913 0.8225 0.1550
-4.000 0.1893 0.01710 0.00757 -0.0912 0.8135 0.1800
-3.750 0.2164 0.01675 0.00732 -0.0908 0.8027 0.2082
-3.500 0.2433 0.01642 0.00710 -0.0905 0.7918 0.2453
-3.250 0.2715 0.01598 0.00686 -0.0903 0.7824 0.3047
-3.000 0.2970 0.01554 0.00676 -0.0898 0.7710 0.3985
-2.750 0.3218 0.01501 0.00669 -0.0889 0.7605 0.5321
-2.500 0.3446 0.01444 0.00662 -0.0870 0.7511 0.6963
-2.250 0.3843 0.01398 0.00658 -0.0879 0.7396 0.9240
-2.000 0.4252 0.01395 0.00637 -0.0904 0.7285 1.0001
-1.750 0.4520 0.01400 0.00622 -0.0900 0.7179 1.0001
-1.500 0.4775 0.01410 0.00619 -0.0894 0.7055 1.0001
-1.250 0.5036 0.01420 0.00615 -0.0889 0.6936 1.0001
-1.000 0.5301 0.01429 0.00609 -0.0885 0.6820 1.0001
-0.750 0.5563 0.01440 0.00607 -0.0880 0.6698 1.0001
-0.500 0.5821 0.01453 0.00610 -0.0876 0.6565 1.0001
-0.250 0.6081 0.01466 0.00613 -0.0871 0.6433 1.0001
0.000 0.6341 0.01481 0.00617 -0.0867 0.6303 1.0001
0.250 0.6603 0.01495 0.00620 -0.0862 0.6172 1.0001
0.500 0.6862 0.01511 0.00626 -0.0858 0.6037 1.0001
0.750 0.7118 0.01530 0.00636 -0.0853 0.5892 1.0001
1.000 0.7373 0.01549 0.00649 -0.0849 0.5750 1.0001
1.250 0.7629 0.01571 0.00663 -0.0844 0.5611 1.0001
1.500 0.7883 0.01594 0.00678 -0.0840 0.5471 1.0001
1.750 0.8136 0.01618 0.00695 -0.0835 0.5334 1.0001
2.000 0.8389 0.01645 0.00713 -0.0831 0.5205 1.0001
2.250 0.8641 0.01673 0.00734 -0.0827 0.5079 1.0001
2.500 0.8890 0.01703 0.00762 -0.0822 0.4949 1.0001
2.750 0.9138 0.01735 0.00789 -0.0818 0.4829 1.0001
3.000 0.9387 0.01769 0.00817 -0.0814 0.4719 1.0001
3.250 0.9633 0.01804 0.00848 -0.0809 0.4605 1.0001
3.500 0.9871 0.01840 0.00882 -0.0804 0.4477 1.0001
3.750 1.0106 0.01876 0.00915 -0.0798 0.4345 1.0001
4.000 1.0337 0.01915 0.00949 -0.0792 0.4216 1.0001
4.250 1.0566 0.01955 0.00983 -0.0785 0.4097 1.0001
4.500 1.0794 0.01995 0.01025 -0.0779 0.3978 1.0001
4.750 1.1022 0.02036 0.01070 -0.0773 0.3870 1.0001
5.000 1.1247 0.02081 0.01111 -0.0766 0.3772 1.0001
5.250 1.1467 0.02124 0.01160 -0.0759 0.3666 1.0001
5.500 1.1686 0.02170 0.01210 -0.0752 0.3568 1.0001
5.750 1.1899 0.02218 0.01259 -0.0744 0.3471 1.0001
6.000 1.2107 0.02266 0.01316 -0.0736 0.3367 1.0001
6.250 1.2309 0.02318 0.01370 -0.0727 0.3271 1.0001
6.500 1.2502 0.02370 0.01430 -0.0717 0.3165 1.0001
6.750 1.2689 0.02425 0.01494 -0.0706 0.3056 1.0001
7.000 1.2864 0.02484 0.01556 -0.0693 0.2950 1.0001
7.250 1.3029 0.02545 0.01623 -0.0679 0.2841 1.0001
7.500 1.3189 0.02609 0.01700 -0.0665 0.2727 1.0001
7.750 1.3333 0.02679 0.01776 -0.0649 0.2617 1.0001
8.000 1.3443 0.02753 0.01853 -0.0627 0.2509 1.0001
8.250 1.3549 0.02835 0.01942 -0.0606 0.2393 1.0001
8.500 1.3651 0.02926 0.02040 -0.0586 0.2282 1.0001
8.750 1.3741 0.03027 0.02147 -0.0566 0.2183 1.0001
9.000 1.3823 0.03139 0.02261 -0.0547 0.2092 1.0001
9.250 1.3917 0.03255 0.02386 -0.0530 0.2009 1.0001
9.500 1.3983 0.03387 0.02518 -0.0512 0.1940 1.0001
9.750 1.4064 0.03521 0.02663 -0.0496 0.1861 1.0001
10.250 1.4157 0.03839 0.02994 -0.0465 0.1709 1.0001
10.500 1.4173 0.04028 0.03181 -0.0451 0.1637 1.0001
10.750 1.4195 0.04225 0.03392 -0.0439 0.1555 1.0001
11.000 1.4197 0.04446 0.03615 -0.0428 0.1487 1.0001
11.250 1.4208 0.04672 0.03855 -0.0420 0.1416 1.0001
11.500 1.4190 0.04930 0.04115 -0.0413 0.1359 1.0001
11.750 1.4190 0.05188 0.04395 -0.0408 0.1292 1.0001
12.000 1.4147 0.05493 0.04704 -0.0405 0.1238 1.0001
12.250 1.4132 0.05789 0.05018 -0.0404 0.1179 1.0001
12.500 1.4087 0.06124 0.05366 -0.0405 0.1128 1.0001
12.750 1.4029 0.06488 0.05739 -0.0407 0.1082 1.0001
13.000 1.3980 0.06865 0.06137 -0.0413 0.1026 1.0001
13.250 1.3882 0.07312 0.06592 -0.0421 0.0978 1.0001
13.500 1.3806 0.07756 0.07055 -0.0432 0.0919 1.0001
13.750 1.3687 0.08275 0.07586 -0.0446 0.0865 1.0001
14.000 1.3575 0.08801 0.08129 -0.0462 0.0805 1.0001
14.250 1.3429 0.09394 0.08732 -0.0482 0.0750 1.0001
14.500 1.3296 0.09985 0.09337 -0.0502 0.0685 1.0001
14.750 1.3140 0.10623 0.09983 -0.0526 0.0629 1.0001
15.000 1.2992 0.11256 0.10625 -0.0550 0.0571 1.0001
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Polar data table (+)
Polar graphs
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