N-22 (n22-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: N-22 (n22-il) Reynolds number: 1,000,000 Max Cl/Cd: 120.47 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-n22-il-1000000.txt Download as CSV file: xf-n22-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.500 -1.0023 0.04268 0.04002 -0.0881 0.9999 0.0206
-16.250 -1.0277 0.03461 0.03167 -0.0977 0.9999 0.0207
-16.000 -1.0333 0.03213 0.02907 -0.0970 0.9999 0.0209
-15.750 -1.0240 0.03078 0.02766 -0.0961 0.9999 0.0212
-15.500 -1.0117 0.02992 0.02676 -0.0948 0.9999 0.0214
-15.250 -0.9997 0.02928 0.02610 -0.0929 0.9999 0.0217
-15.000 -0.9901 0.02865 0.02543 -0.0905 0.9999 0.0220
-14.750 -0.9824 0.02800 0.02473 -0.0878 0.9999 0.0222
-14.500 -0.9652 0.02717 0.02381 -0.0868 0.9993 0.0226
-14.250 -0.9372 0.02607 0.02259 -0.0881 0.9977 0.0231
-14.000 -0.9085 0.02500 0.02139 -0.0893 0.9961 0.0235
-13.750 -0.8782 0.02412 0.02038 -0.0905 0.9947 0.0239
-13.500 -0.8461 0.02355 0.01970 -0.0918 0.9936 0.0241
-13.250 -0.8250 0.02114 0.01709 -0.0926 0.9906 0.0249
-13.000 -0.7939 0.02061 0.01655 -0.0936 0.9887 0.0254
-12.750 -0.7617 0.02009 0.01600 -0.0947 0.9871 0.0258
-12.500 -0.7297 0.01947 0.01531 -0.0959 0.9854 0.0263
-12.250 -0.6981 0.01881 0.01457 -0.0969 0.9834 0.0268
-12.000 -0.6691 0.01826 0.01393 -0.0973 0.9799 0.0274
-11.750 -0.6414 0.01777 0.01335 -0.0973 0.9751 0.0279
-11.500 -0.6132 0.01732 0.01281 -0.0973 0.9709 0.0282
-11.250 -0.5882 0.01676 0.01215 -0.0968 0.9650 0.0285
-11.000 -0.5676 0.01533 0.01059 -0.0958 0.9581 0.0293
-10.750 -0.5428 0.01487 0.01010 -0.0951 0.9520 0.0299
-10.500 -0.5178 0.01452 0.00971 -0.0943 0.9448 0.0304
-10.250 -0.4926 0.01413 0.00926 -0.0936 0.9384 0.0309
-10.000 -0.4670 0.01370 0.00878 -0.0930 0.9306 0.0314
-9.750 -0.4415 0.01330 0.00829 -0.0923 0.9235 0.0319
-9.500 -0.4150 0.01293 0.00785 -0.0918 0.9151 0.0325
-9.250 -0.3886 0.01265 0.00749 -0.0912 0.9072 0.0330
-9.000 -0.3614 0.01238 0.00716 -0.0909 0.8980 0.0333
-8.750 -0.3362 0.01162 0.00630 -0.0903 0.8889 0.0341
-8.500 -0.3098 0.01113 0.00575 -0.0899 0.8788 0.0348
-8.250 -0.2826 0.01082 0.00540 -0.0895 0.8687 0.0355
-8.000 -0.2554 0.01058 0.00509 -0.0892 0.8582 0.0362
-7.750 -0.2276 0.01035 0.00481 -0.0889 0.8469 0.0370
-7.500 -0.1998 0.01015 0.00454 -0.0886 0.8357 0.0379
-7.250 -0.1721 0.00996 0.00427 -0.0884 0.8243 0.0386
-7.000 -0.1441 0.00980 0.00404 -0.0881 0.8120 0.0391
-6.750 -0.1168 0.00939 0.00356 -0.0879 0.7992 0.0405
-6.500 -0.0889 0.00919 0.00330 -0.0877 0.7871 0.0418
-6.250 -0.0607 0.00905 0.00311 -0.0875 0.7762 0.0431
-6.000 -0.0323 0.00892 0.00293 -0.0875 0.7660 0.0446
-5.750 -0.0037 0.00883 0.00279 -0.0874 0.7567 0.0457
-5.500 0.0245 0.00859 0.00251 -0.0873 0.7473 0.0489
-5.250 0.0531 0.00846 0.00237 -0.0873 0.7384 0.0516
-4.750 0.1102 0.00820 0.00206 -0.0872 0.7203 0.0601
-4.500 0.1387 0.00809 0.00193 -0.0872 0.7118 0.0674
-4.250 0.1674 0.00794 0.00184 -0.0873 0.7031 0.0803
-4.000 0.1959 0.00784 0.00176 -0.0873 0.6941 0.0990
-3.750 0.2245 0.00773 0.00170 -0.0873 0.6847 0.1168
-3.500 0.2532 0.00767 0.00165 -0.0874 0.6761 0.1323
-3.250 0.2819 0.00760 0.00161 -0.0875 0.6668 0.1482
-3.000 0.3105 0.00753 0.00157 -0.0876 0.6574 0.1671
-2.750 0.3389 0.00748 0.00154 -0.0876 0.6469 0.1911
-2.500 0.3675 0.00737 0.00152 -0.0877 0.6360 0.2249
-2.250 0.3957 0.00724 0.00150 -0.0878 0.6256 0.2761
-2.000 0.4236 0.00707 0.00151 -0.0879 0.6143 0.3493
-1.750 0.4516 0.00685 0.00153 -0.0881 0.6026 0.4408
-1.500 0.4789 0.00660 0.00156 -0.0881 0.5900 0.5572
-1.250 0.5051 0.00629 0.00163 -0.0878 0.5767 0.7015
-1.000 0.5270 0.00591 0.00172 -0.0863 0.5629 0.8705
-0.750 0.5587 0.00585 0.00176 -0.0868 0.5482 0.9797
-0.500 0.5983 0.00597 0.00179 -0.0894 0.5322 1.0001
-0.250 0.6251 0.00610 0.00184 -0.0892 0.5169 1.0001
0.000 0.6519 0.00625 0.00189 -0.0890 0.5008 1.0001
0.250 0.6787 0.00640 0.00195 -0.0888 0.4844 1.0001
0.500 0.7057 0.00656 0.00203 -0.0887 0.4688 1.0001
0.750 0.7327 0.00673 0.00211 -0.0886 0.4538 1.0001
1.000 0.7594 0.00692 0.00221 -0.0884 0.4365 1.0001
1.250 0.7860 0.00713 0.00231 -0.0883 0.4161 1.0001
1.500 0.8126 0.00734 0.00242 -0.0882 0.3976 1.0001
1.750 0.8395 0.00753 0.00254 -0.0881 0.3844 1.0001
2.250 0.8937 0.00786 0.00277 -0.0881 0.3639 1.0001
2.500 0.9206 0.00805 0.00291 -0.0880 0.3545 1.0001
2.750 0.9476 0.00821 0.00304 -0.0880 0.3455 1.0001
3.000 0.9746 0.00839 0.00317 -0.0880 0.3380 1.0001
3.250 1.0016 0.00855 0.00331 -0.0881 0.3307 1.0001
3.500 1.0283 0.00874 0.00347 -0.0880 0.3236 1.0001
3.750 1.0554 0.00889 0.00361 -0.0881 0.3172 1.0001
4.250 1.1086 0.00925 0.00394 -0.0881 0.3029 1.0001
4.500 1.1346 0.00948 0.00413 -0.0880 0.2949 1.0001
4.750 1.1613 0.00964 0.00430 -0.0880 0.2884 1.0001
5.000 1.1871 0.00986 0.00449 -0.0879 0.2804 1.0001
5.250 1.2131 0.01007 0.00468 -0.0879 0.2713 1.0001
5.500 1.2382 0.01034 0.00491 -0.0877 0.2593 1.0001
5.750 1.2628 0.01064 0.00515 -0.0874 0.2452 1.0001
6.000 1.2868 0.01098 0.00541 -0.0871 0.2287 1.0001
6.250 1.3095 0.01140 0.00574 -0.0866 0.2083 1.0001
6.500 1.3307 0.01193 0.00614 -0.0858 0.1859 1.0001
6.750 1.3515 0.01246 0.00656 -0.0850 0.1665 1.0001
7.000 1.3719 0.01300 0.00701 -0.0842 0.1506 1.0001
7.250 1.3932 0.01345 0.00741 -0.0834 0.1398 1.0001
7.500 1.4141 0.01391 0.00783 -0.0827 0.1305 1.0001
7.750 1.4348 0.01436 0.00825 -0.0819 0.1226 1.0001
8.000 1.4555 0.01478 0.00865 -0.0811 0.1158 1.0001
8.250 1.4744 0.01527 0.00912 -0.0800 0.1086 1.0001
8.500 1.4942 0.01567 0.00953 -0.0791 0.1037 1.0001
8.750 1.5100 0.01618 0.01001 -0.0775 0.0971 1.0001
9.000 1.5266 0.01666 0.01049 -0.0760 0.0913 1.0001
9.250 1.5404 0.01731 0.01111 -0.0742 0.0833 1.0001
9.500 1.5535 0.01802 0.01177 -0.0724 0.0736 1.0001
9.750 1.5591 0.01920 0.01282 -0.0697 0.0541 1.0001
10.000 1.5524 0.02121 0.01464 -0.0656 0.0293 1.0001
10.250 1.5572 0.02259 0.01600 -0.0632 0.0229 1.0001
10.500 1.5644 0.02387 0.01732 -0.0613 0.0200 1.0001
10.750 1.5746 0.02499 0.01848 -0.0599 0.0187 1.0001
11.000 1.5826 0.02632 0.01986 -0.0584 0.0175 1.0001
11.250 1.5880 0.02790 0.02150 -0.0568 0.0164 1.0001
11.500 1.5974 0.02923 0.02289 -0.0558 0.0159 1.0001
11.750 1.6051 0.03074 0.02448 -0.0547 0.0153 1.0001
12.000 1.6113 0.03244 0.02624 -0.0537 0.0148 1.0001
12.250 1.6150 0.03442 0.02828 -0.0527 0.0142 1.0001
12.500 1.6148 0.03687 0.03081 -0.0517 0.0137 1.0001
12.750 1.6171 0.03914 0.03317 -0.0509 0.0133 1.0001
13.000 1.6207 0.04133 0.03545 -0.0504 0.0131 1.0001
13.250 1.6227 0.04377 0.03797 -0.0500 0.0128 1.0001
13.500 1.6231 0.04647 0.04076 -0.0497 0.0125 1.0001
13.750 1.6223 0.04936 0.04374 -0.0495 0.0123 1.0001
14.000 1.6202 0.05251 0.04698 -0.0495 0.0120 1.0001
14.250 1.6162 0.05601 0.05057 -0.0496 0.0118 1.0001
14.500 1.6100 0.05988 0.05454 -0.0499 0.0116 1.0001
14.750 1.6009 0.06423 0.05899 -0.0504 0.0114 1.0001
15.000 1.5892 0.06908 0.06395 -0.0512 0.0112 1.0001
15.250 1.5737 0.07462 0.06962 -0.0523 0.0111 1.0001
15.500 1.5564 0.08052 0.07564 -0.0536 0.0109 1.0001
15.750 1.5440 0.08583 0.08107 -0.0549 0.0109 1.0001
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