N-22 (n22-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: N-22 (n22-il) Reynolds number: 100,000 Max Cl/Cd: 51.81 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-n22-il-100000.txt Download as CSV file: xf-n22-il-100000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.3285 0.09633 0.09143 -0.0339 0.9999 0.1364
-10.000 -0.3554 0.09537 0.09062 -0.0331 0.9999 0.1397
-9.750 -0.3956 0.09529 0.09073 -0.0302 0.9999 0.1406
-9.500 -0.4384 0.09431 0.08989 -0.0317 0.9999 0.1413
-9.250 -0.4412 0.09067 0.08632 -0.0287 0.9999 0.1427
-9.000 -0.4226 0.08847 0.08414 -0.0224 0.9999 0.1452
-8.750 -0.4284 0.08682 0.08254 -0.0196 0.9999 0.1475
-8.500 -0.4393 0.08501 0.08079 -0.0181 0.9999 0.1503
-8.000 -0.4607 0.07763 0.07340 -0.0261 0.9981 0.1596
-7.750 -0.4283 0.07266 0.06806 -0.0398 0.9891 0.1743
-7.500 -0.4031 0.06881 0.06440 -0.0376 0.9851 0.1766
-7.250 -0.3739 0.06627 0.06185 -0.0388 0.9792 0.1843
-7.000 -0.3438 0.06180 0.05725 -0.0453 0.9718 0.1960
-6.750 -0.2958 0.04018 0.03342 -0.0660 0.9658 0.1097
-6.500 -0.2595 0.03685 0.02960 -0.0690 0.9592 0.1097
-6.250 -0.2155 0.03375 0.02598 -0.0730 0.9551 0.1094
-6.000 -0.1842 0.03169 0.02345 -0.0741 0.9465 0.1101
-5.750 -0.1409 0.02970 0.02118 -0.0775 0.9413 0.1139
-5.500 -0.1073 0.02870 0.02009 -0.0788 0.9330 0.1183
-5.250 -0.0643 0.02740 0.01845 -0.0815 0.9267 0.1234
-5.000 -0.0259 0.02628 0.01723 -0.0834 0.9195 0.1304
-4.750 0.0136 0.02553 0.01630 -0.0854 0.9115 0.1409
-4.500 0.0646 0.02439 0.01517 -0.0894 0.9075 0.1570
-4.250 0.0929 0.02373 0.01458 -0.0894 0.8963 0.1745
-4.000 0.1431 0.02252 0.01362 -0.0932 0.8920 0.2111
-3.750 0.1712 0.02189 0.01322 -0.0931 0.8808 0.2506
-3.500 0.2154 0.02076 0.01247 -0.0955 0.8757 0.3223
-3.250 0.2404 0.01990 0.01227 -0.0948 0.8643 0.4414
-3.000 0.3018 0.01788 0.01181 -0.0981 0.8611 1.0001
-2.750 0.3294 0.01788 0.01154 -0.0978 0.8494 1.0001
-2.500 0.3691 0.01750 0.01092 -0.0991 0.8429 1.0001
-2.250 0.3934 0.01754 0.01079 -0.0982 0.8300 1.0001
-2.000 0.4208 0.01751 0.01061 -0.0976 0.8187 1.0001
-1.750 0.4554 0.01719 0.01011 -0.0980 0.8107 1.0001
-1.500 0.4799 0.01724 0.01004 -0.0970 0.7975 1.0001
-1.250 0.5065 0.01723 0.00991 -0.0962 0.7852 1.0001
-1.000 0.5361 0.01709 0.00964 -0.0959 0.7746 1.0001
-0.750 0.5645 0.01700 0.00943 -0.0953 0.7628 1.0001
-0.500 0.5900 0.01706 0.00939 -0.0945 0.7489 1.0001
-0.250 0.6163 0.01710 0.00934 -0.0937 0.7352 1.0001
0.000 0.6432 0.01712 0.00926 -0.0930 0.7218 1.0001
0.250 0.6709 0.01714 0.00916 -0.0925 0.7087 1.0001
0.500 0.6993 0.01713 0.00903 -0.0920 0.6957 1.0001
0.750 0.7250 0.01726 0.00907 -0.0913 0.6804 1.0001
1.000 0.7506 0.01741 0.00916 -0.0906 0.6651 1.0001
1.250 0.7764 0.01759 0.00927 -0.0900 0.6500 1.0001
1.500 0.8022 0.01778 0.00939 -0.0894 0.6350 1.0001
1.750 0.8281 0.01800 0.00953 -0.0888 0.6201 1.0001
2.000 0.8540 0.01825 0.00972 -0.0883 0.6059 1.0001
2.250 0.8802 0.01851 0.00991 -0.0879 0.5923 1.0001
2.500 0.9070 0.01876 0.01007 -0.0876 0.5795 1.0001
2.750 0.9333 0.01905 0.01030 -0.0872 0.5667 1.0001
3.000 0.9578 0.01943 0.01068 -0.0867 0.5531 1.0001
3.250 0.9826 0.01978 0.01099 -0.0861 0.5396 1.0001
3.500 1.0076 0.02009 0.01127 -0.0856 0.5263 1.0001
3.750 1.0330 0.02039 0.01150 -0.0851 0.5132 1.0001
4.000 1.0596 0.02068 0.01168 -0.0848 0.5011 1.0001
4.250 1.0826 0.02108 0.01214 -0.0841 0.4878 1.0001
4.500 1.1059 0.02152 0.01261 -0.0835 0.4755 1.0001
4.750 1.1305 0.02195 0.01302 -0.0830 0.4640 1.0001
5.000 1.1570 0.02233 0.01331 -0.0828 0.4530 1.0001
5.250 1.1783 0.02282 0.01391 -0.0819 0.4406 1.0001
5.500 1.2008 0.02333 0.01447 -0.0812 0.4288 1.0001
5.750 1.2249 0.02380 0.01493 -0.0807 0.4173 1.0001
6.000 1.2492 0.02425 0.01533 -0.0803 0.4054 1.0001
6.250 1.2690 0.02479 0.01599 -0.0792 0.3923 1.0001
6.500 1.2893 0.02533 0.01659 -0.0782 0.3790 1.0001
6.750 1.3097 0.02588 0.01719 -0.0772 0.3654 1.0001
7.000 1.3298 0.02645 0.01777 -0.0761 0.3514 1.0001
7.250 1.3494 0.02708 0.01839 -0.0750 0.3372 1.0001
7.500 1.3682 0.02774 0.01906 -0.0738 0.3226 1.0001
7.750 1.3862 0.02845 0.01975 -0.0726 0.3079 1.0001
8.000 1.4037 0.02920 0.02047 -0.0712 0.2937 1.0001
8.250 1.4173 0.03005 0.02143 -0.0694 0.2801 1.0001
8.500 1.4314 0.03104 0.02254 -0.0677 0.2681 1.0001
8.750 1.4480 0.03203 0.02357 -0.0664 0.2577 1.0001
9.000 1.4676 0.03280 0.02422 -0.0655 0.2476 1.0001
9.250 1.4738 0.03375 0.02540 -0.0628 0.2375 1.0001
9.500 1.4831 0.03458 0.02627 -0.0606 0.2279 1.0001
9.750 1.4937 0.03520 0.02681 -0.0586 0.2182 1.0001
10.000 1.4908 0.03627 0.02810 -0.0548 0.2099 1.0001
10.250 1.4968 0.03717 0.02896 -0.0524 0.2016 1.0001
10.500 1.4959 0.03841 0.03036 -0.0495 0.1937 1.0001
10.750 1.4998 0.03967 0.03164 -0.0474 0.1862 1.0001
11.000 1.5004 0.04114 0.03325 -0.0452 0.1790 1.0001
11.250 1.5042 0.04266 0.03482 -0.0435 0.1722 1.0001
11.500 1.5021 0.04449 0.03683 -0.0415 0.1654 1.0001
11.750 1.5026 0.04632 0.03869 -0.0400 0.1583 1.0001
12.000 1.4961 0.04867 0.04122 -0.0384 0.1512 1.0001
12.250 1.4911 0.05109 0.04372 -0.0371 0.1438 1.0001
12.500 1.4812 0.05404 0.04680 -0.0361 0.1360 1.0001
12.750 1.4687 0.05756 0.05048 -0.0355 0.1278 1.0001
13.000 1.4564 0.06115 0.05404 -0.0351 0.1187 1.0001
13.250 1.4374 0.06594 0.05903 -0.0353 0.1098 1.0001
13.500 1.4189 0.07105 0.06423 -0.0359 0.1005 1.0001
13.750 1.4037 0.07596 0.06911 -0.0366 0.0923 1.0001
14.000 1.3890 0.08117 0.07440 -0.0378 0.0853 1.0001
14.250 1.3769 0.08616 0.07946 -0.0387 0.0794 1.0001
14.500 1.3679 0.09081 0.08414 -0.0399 0.0745 1.0001
14.750 1.3617 0.09505 0.08843 -0.0407 0.0705 1.0001
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Polar data table (+)
Polar graphs
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