N-22 (n22-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: N-22 (n22-il) Reynolds number: 500,000 Max Cl/Cd: 94.56 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-n22-il-500000-n5.txt Download as CSV file: xf-n22-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.250 -0.9035 0.03928 0.03606 -0.0926 0.9999 0.0226
-15.000 -0.9201 0.03558 0.03213 -0.0927 0.9999 0.0228
-14.750 -0.9252 0.03320 0.02955 -0.0911 0.9999 0.0231
-14.500 -0.9265 0.03138 0.02752 -0.0888 0.9999 0.0234
-14.250 -0.9067 0.02941 0.02531 -0.0900 0.9968 0.0238
-14.000 -0.8808 0.02811 0.02394 -0.0913 0.9942 0.0242
-13.750 -0.8538 0.02720 0.02296 -0.0922 0.9913 0.0246
-13.500 -0.8260 0.02635 0.02204 -0.0931 0.9882 0.0251
-13.250 -0.7973 0.02548 0.02107 -0.0942 0.9854 0.0256
-13.000 -0.7690 0.02454 0.02000 -0.0951 0.9826 0.0261
-12.750 -0.7436 0.02354 0.01885 -0.0955 0.9778 0.0267
-12.500 -0.7162 0.02251 0.01765 -0.0961 0.9739 0.0273
-12.250 -0.6889 0.02162 0.01657 -0.0966 0.9697 0.0278
-12.000 -0.6631 0.02087 0.01566 -0.0965 0.9640 0.0282
-11.750 -0.6373 0.01975 0.01445 -0.0967 0.9593 0.0287
-11.500 -0.6124 0.01911 0.01375 -0.0964 0.9528 0.0292
-11.250 -0.5861 0.01860 0.01317 -0.0961 0.9467 0.0297
-11.000 -0.5603 0.01807 0.01257 -0.0958 0.9406 0.0302
-10.750 -0.5352 0.01750 0.01190 -0.0953 0.9331 0.0307
-10.500 -0.5096 0.01692 0.01122 -0.0948 0.9266 0.0311
-10.250 -0.4844 0.01638 0.01058 -0.0942 0.9183 0.0317
-10.000 -0.4586 0.01589 0.00998 -0.0937 0.9111 0.0322
-9.750 -0.4327 0.01543 0.00941 -0.0932 0.9021 0.0328
-9.500 -0.4066 0.01497 0.00883 -0.0927 0.8939 0.0331
-9.250 -0.3807 0.01445 0.00822 -0.0922 0.8845 0.0335
-9.000 -0.3549 0.01389 0.00760 -0.0918 0.8754 0.0341
-8.750 -0.3285 0.01348 0.00713 -0.0913 0.8656 0.0347
-8.500 -0.3016 0.01314 0.00672 -0.0910 0.8557 0.0353
-8.250 -0.2746 0.01283 0.00633 -0.0906 0.8460 0.0359
-8.000 -0.2474 0.01254 0.00598 -0.0903 0.8354 0.0367
-7.750 -0.2200 0.01228 0.00564 -0.0900 0.8252 0.0376
-7.500 -0.1927 0.01202 0.00528 -0.0897 0.8149 0.0383
-7.250 -0.1651 0.01177 0.00495 -0.0894 0.8040 0.0390
-7.000 -0.1376 0.01150 0.00461 -0.0891 0.7936 0.0397
-6.750 -0.1103 0.01123 0.00427 -0.0889 0.7829 0.0409
-6.500 -0.0825 0.01102 0.00402 -0.0887 0.7717 0.0421
-6.250 -0.0546 0.01085 0.00379 -0.0885 0.7606 0.0435
-6.000 -0.0269 0.01071 0.00356 -0.0883 0.7483 0.0450
-5.750 0.0010 0.01059 0.00336 -0.0881 0.7355 0.0465
-5.500 0.0290 0.01039 0.00314 -0.0880 0.7244 0.0493
-5.250 0.0571 0.01026 0.00297 -0.0879 0.7150 0.0521
-5.000 0.0854 0.01016 0.00281 -0.0878 0.7053 0.0548
-4.750 0.1136 0.01001 0.00265 -0.0877 0.6965 0.0595
-4.500 0.1418 0.00991 0.00252 -0.0877 0.6871 0.0647
-4.250 0.1701 0.00979 0.00241 -0.0877 0.6776 0.0737
-4.000 0.1982 0.00969 0.00232 -0.0876 0.6682 0.0866
-3.750 0.2266 0.00959 0.00225 -0.0876 0.6587 0.1016
-3.500 0.2548 0.00952 0.00218 -0.0876 0.6489 0.1160
-3.250 0.2830 0.00946 0.00213 -0.0876 0.6379 0.1302
-3.000 0.3112 0.00940 0.00208 -0.0876 0.6269 0.1461
-2.750 0.3393 0.00934 0.00205 -0.0876 0.6165 0.1653
-2.500 0.3673 0.00928 0.00202 -0.0876 0.6049 0.1901
-2.250 0.3952 0.00920 0.00200 -0.0876 0.5924 0.2213
-2.000 0.4229 0.00912 0.00200 -0.0877 0.5790 0.2638
-1.750 0.4503 0.00897 0.00202 -0.0877 0.5657 0.3354
-1.500 0.4773 0.00877 0.00206 -0.0877 0.5527 0.4286
-1.000 0.5305 0.00845 0.00217 -0.0874 0.5248 0.6129
-0.750 0.5559 0.00828 0.00225 -0.0869 0.5099 0.7125
-0.500 0.5788 0.00808 0.00234 -0.0856 0.4953 0.8247
-0.250 0.6082 0.00800 0.00243 -0.0855 0.4809 0.9540
0.000 0.6461 0.00814 0.00248 -0.0878 0.4663 1.0001
0.250 0.6727 0.00830 0.00256 -0.0876 0.4535 1.0001
0.500 0.6992 0.00848 0.00265 -0.0874 0.4404 1.0001
0.750 0.7257 0.00867 0.00275 -0.0872 0.4274 1.0001
1.000 0.7525 0.00883 0.00285 -0.0871 0.4160 1.0001
1.250 0.7792 0.00901 0.00297 -0.0870 0.4062 1.0001
1.500 0.8056 0.00921 0.00309 -0.0868 0.3956 1.0001
1.750 0.8319 0.00941 0.00323 -0.0866 0.3822 1.0001
2.000 0.8576 0.00967 0.00339 -0.0864 0.3653 1.0001
2.250 0.8834 0.00991 0.00355 -0.0862 0.3507 1.0001
2.500 0.9096 0.01013 0.00371 -0.0860 0.3411 1.0001
2.750 0.9358 0.01034 0.00388 -0.0859 0.3324 1.0001
3.000 0.9621 0.01053 0.00405 -0.0858 0.3252 1.0001
3.250 0.9881 0.01075 0.00423 -0.0857 0.3171 1.0001
3.500 1.0142 0.01096 0.00442 -0.0855 0.3098 1.0001
3.750 1.0401 0.01117 0.00462 -0.0854 0.3025 1.0001
4.000 1.0657 0.01140 0.00483 -0.0852 0.2962 1.0001
4.250 1.0916 0.01160 0.00503 -0.0851 0.2892 1.0001
4.500 1.1167 0.01186 0.00528 -0.0848 0.2820 1.0001
4.750 1.1423 0.01208 0.00550 -0.0847 0.2745 1.0001
5.000 1.1668 0.01236 0.00575 -0.0844 0.2658 1.0001
5.250 1.1914 0.01263 0.00602 -0.0841 0.2552 1.0001
5.500 1.2155 0.01293 0.00630 -0.0838 0.2442 1.0001
5.750 1.2389 0.01327 0.00660 -0.0833 0.2324 1.0001
6.000 1.2615 0.01366 0.00693 -0.0828 0.2183 1.0001
6.250 1.2826 0.01413 0.00733 -0.0820 0.1996 1.0001
6.500 1.3016 0.01475 0.00782 -0.0809 0.1787 1.0001
6.750 1.3207 0.01533 0.00832 -0.0799 0.1622 1.0001
7.000 1.3396 0.01589 0.00882 -0.0788 0.1504 1.0001
7.250 1.3590 0.01639 0.00931 -0.0778 0.1409 1.0001
7.500 1.3771 0.01692 0.00982 -0.0766 0.1323 1.0001
7.750 1.3930 0.01747 0.01036 -0.0750 0.1247 1.0001
8.000 1.4096 0.01799 0.01088 -0.0736 0.1185 1.0001
8.250 1.4243 0.01863 0.01151 -0.0719 0.1112 1.0001
8.500 1.4404 0.01920 0.01210 -0.0706 0.1056 1.0001
8.750 1.4551 0.01988 0.01278 -0.0691 0.0998 1.0001
9.000 1.4699 0.02056 0.01348 -0.0677 0.0947 1.0001
9.250 1.4841 0.02129 0.01424 -0.0663 0.0888 1.0001
9.500 1.4970 0.02213 0.01508 -0.0648 0.0828 1.0001
9.750 1.5079 0.02313 0.01606 -0.0632 0.0744 1.0001
10.000 1.5172 0.02426 0.01716 -0.0616 0.0638 1.0001
10.500 1.5127 0.02845 0.02112 -0.0567 0.0283 1.0001
10.750 1.5158 0.03028 0.02300 -0.0551 0.0231 1.0001
11.000 1.5206 0.03208 0.02484 -0.0538 0.0201 1.0001
11.250 1.5258 0.03388 0.02671 -0.0527 0.0183 1.0001
11.500 1.5303 0.03582 0.02872 -0.0518 0.0169 1.0001
11.750 1.5334 0.03797 0.03093 -0.0509 0.0158 1.0001
12.000 1.5378 0.04004 0.03310 -0.0503 0.0151 1.0001
12.250 1.5406 0.04234 0.03549 -0.0497 0.0144 1.0001
12.500 1.5418 0.04488 0.03812 -0.0492 0.0138 1.0001
12.750 1.5412 0.04768 0.04101 -0.0489 0.0133 1.0001
13.000 1.5387 0.05080 0.04422 -0.0487 0.0129 1.0001
13.250 1.5371 0.05393 0.04746 -0.0487 0.0126 1.0001
13.500 1.5355 0.05715 0.05079 -0.0488 0.0123 1.0001
13.750 1.5323 0.06065 0.05441 -0.0491 0.0120 1.0001
14.000 1.5278 0.06441 0.05828 -0.0496 0.0118 1.0001
14.250 1.5224 0.06842 0.06240 -0.0502 0.0115 1.0001
14.500 1.5155 0.07271 0.06680 -0.0510 0.0113 1.0001
14.750 1.5072 0.07729 0.07151 -0.0519 0.0111 1.0001
15.000 1.4979 0.08209 0.07642 -0.0531 0.0109 1.0001
15.250 1.4874 0.08719 0.08163 -0.0544 0.0107 1.0001
15.500 1.4757 0.09252 0.08708 -0.0558 0.0105 1.0001
15.750 1.4628 0.09810 0.09278 -0.0575 0.0104 1.0001
16.000 1.4490 0.10395 0.09875 -0.0593 0.0102 1.0001
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Polar data table (+)
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