N-22 (n22-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: N-22 (n22-il) Reynolds number: 1,000,000 Max Cl/Cd: 112.79 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-n22-il-1000000-n5.txt Download as CSV file: xf-n22-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.750 -1.2106 0.03148 0.02825 -0.1017 0.9999 0.0157
-17.500 -1.2048 0.02967 0.02630 -0.1010 0.9999 0.0160
-17.250 -1.1945 0.02818 0.02468 -0.1002 0.9999 0.0163
-17.000 -1.1819 0.02688 0.02329 -0.0992 0.9999 0.0166
-16.750 -1.1669 0.02586 0.02222 -0.0982 0.9999 0.0171
-16.500 -1.1512 0.02501 0.02132 -0.0968 0.9999 0.0175
-16.250 -1.1364 0.02426 0.02051 -0.0952 0.9999 0.0180
-16.000 -1.1117 0.02345 0.01963 -0.0954 0.9980 0.0185
-15.750 -1.0848 0.02262 0.01870 -0.0959 0.9959 0.0190
-15.500 -1.0571 0.02181 0.01780 -0.0965 0.9941 0.0194
-15.250 -1.0307 0.02108 0.01697 -0.0968 0.9911 0.0197
-15.000 -1.0044 0.02029 0.01610 -0.0970 0.9878 0.0200
-14.750 -0.9764 0.01962 0.01539 -0.0975 0.9849 0.0205
-14.500 -0.9486 0.01910 0.01482 -0.0977 0.9817 0.0209
-14.250 -0.9217 0.01864 0.01432 -0.0976 0.9773 0.0214
-14.000 -0.8942 0.01817 0.01379 -0.0977 0.9733 0.0219
-13.750 -0.8681 0.01768 0.01324 -0.0974 0.9689 0.0223
-13.500 -0.8427 0.01721 0.01270 -0.0970 0.9633 0.0227
-13.250 -0.8168 0.01679 0.01219 -0.0966 0.9584 0.0231
-13.000 -0.7915 0.01639 0.01173 -0.0960 0.9526 0.0234
-12.750 -0.7662 0.01600 0.01126 -0.0954 0.9466 0.0236
-12.500 -0.7417 0.01544 0.01062 -0.0948 0.9408 0.0240
-12.250 -0.7167 0.01495 0.01007 -0.0942 0.9340 0.0245
-12.000 -0.6912 0.01458 0.00965 -0.0936 0.9277 0.0250
-11.750 -0.6648 0.01425 0.00928 -0.0932 0.9205 0.0254
-11.500 -0.6387 0.01394 0.00891 -0.0927 0.9131 0.0258
-11.250 -0.6122 0.01360 0.00851 -0.0923 0.9053 0.0262
-11.000 -0.5858 0.01329 0.00812 -0.0918 0.8968 0.0266
-10.750 -0.5589 0.01298 0.00774 -0.0914 0.8881 0.0271
-10.500 -0.5324 0.01266 0.00734 -0.0910 0.8787 0.0274
-10.250 -0.5053 0.01236 0.00696 -0.0906 0.8688 0.0277
-10.000 -0.4782 0.01209 0.00660 -0.0902 0.8588 0.0279
-9.500 -0.4241 0.01145 0.00580 -0.0896 0.8374 0.0288
-9.250 -0.3968 0.01114 0.00542 -0.0893 0.8270 0.0293
-8.750 -0.3415 0.01067 0.00483 -0.0888 0.8051 0.0302
-8.500 -0.3137 0.01047 0.00457 -0.0886 0.7945 0.0307
-8.000 -0.2576 0.01011 0.00408 -0.0882 0.7730 0.0316
-7.750 -0.2295 0.00995 0.00385 -0.0880 0.7625 0.0321
-7.500 -0.2014 0.00981 0.00364 -0.0879 0.7514 0.0327
-7.250 -0.1730 0.00968 0.00345 -0.0878 0.7407 0.0332
-7.000 -0.1448 0.00952 0.00322 -0.0876 0.7292 0.0338
-6.750 -0.1168 0.00937 0.00301 -0.0875 0.7158 0.0348
-6.500 -0.0885 0.00925 0.00284 -0.0874 0.7030 0.0358
-6.250 -0.0599 0.00913 0.00269 -0.0874 0.6930 0.0368
-6.000 -0.0314 0.00903 0.00254 -0.0873 0.6841 0.0379
-5.750 -0.0027 0.00893 0.00241 -0.0873 0.6754 0.0389
-5.500 0.0259 0.00883 0.00227 -0.0873 0.6667 0.0405
-5.250 0.0546 0.00873 0.00215 -0.0873 0.6570 0.0428
-5.000 0.0832 0.00865 0.00205 -0.0873 0.6483 0.0452
-4.750 0.1120 0.00858 0.00195 -0.0873 0.6390 0.0480
-4.500 0.1406 0.00850 0.00186 -0.0873 0.6293 0.0520
-4.250 0.1692 0.00846 0.00178 -0.0873 0.6183 0.0556
-4.000 0.1978 0.00839 0.00170 -0.0874 0.6072 0.0619
-3.750 0.2264 0.00832 0.00164 -0.0874 0.5971 0.0707
-3.500 0.2548 0.00826 0.00159 -0.0875 0.5859 0.0837
-3.250 0.2832 0.00822 0.00156 -0.0875 0.5729 0.0974
-3.000 0.3116 0.00820 0.00153 -0.0876 0.5593 0.1105
-2.750 0.3400 0.00819 0.00151 -0.0877 0.5461 0.1236
-2.500 0.3684 0.00819 0.00151 -0.0877 0.5335 0.1361
-2.250 0.3967 0.00820 0.00151 -0.0878 0.5204 0.1511
-2.000 0.4248 0.00819 0.00152 -0.0878 0.5061 0.1745
-1.500 0.4807 0.00817 0.00157 -0.0880 0.4756 0.2384
-1.250 0.5086 0.00812 0.00161 -0.0881 0.4618 0.2899
-1.000 0.5364 0.00802 0.00166 -0.0882 0.4492 0.3632
-0.750 0.5641 0.00797 0.00172 -0.0883 0.4372 0.4236
-0.500 0.5917 0.00792 0.00179 -0.0884 0.4251 0.4873
-0.250 0.6191 0.00783 0.00188 -0.0884 0.4127 0.5704
0.000 0.6463 0.00776 0.00197 -0.0884 0.4013 0.6465
0.250 0.6734 0.00772 0.00206 -0.0883 0.3914 0.7123
0.500 0.6989 0.00757 0.00217 -0.0879 0.3823 0.8101
0.750 0.7213 0.00737 0.00228 -0.0864 0.3745 0.9526
1.000 0.7586 0.00753 0.00237 -0.0886 0.3610 1.0001
1.250 0.7852 0.00774 0.00248 -0.0885 0.3442 1.0001
1.500 0.8118 0.00795 0.00260 -0.0884 0.3291 1.0001
1.750 0.8390 0.00811 0.00270 -0.0884 0.3192 1.0001
2.000 0.8661 0.00827 0.00282 -0.0884 0.3118 1.0001
2.250 0.8934 0.00841 0.00293 -0.0884 0.3046 1.0001
2.500 0.9203 0.00859 0.00306 -0.0884 0.2973 1.0001
2.750 0.9477 0.00873 0.00318 -0.0884 0.2915 1.0001
3.000 0.9746 0.00890 0.00332 -0.0884 0.2851 1.0001
3.250 1.0017 0.00905 0.00346 -0.0885 0.2796 1.0001
3.500 1.0286 0.00921 0.00360 -0.0885 0.2731 1.0001
3.750 1.0550 0.00941 0.00377 -0.0884 0.2662 1.0001
4.000 1.0816 0.00959 0.00393 -0.0884 0.2581 1.0001
4.250 1.1076 0.00982 0.00411 -0.0883 0.2486 1.0001
4.500 1.1331 0.01008 0.00432 -0.0882 0.2375 1.0001
4.750 1.1588 0.01032 0.00452 -0.0881 0.2265 1.0001
5.000 1.1836 0.01061 0.00476 -0.0878 0.2133 1.0001
5.250 1.2075 0.01098 0.00505 -0.0875 0.1966 1.0001
5.500 1.2299 0.01146 0.00540 -0.0869 0.1760 1.0001
5.750 1.2521 0.01194 0.00577 -0.0863 0.1577 1.0001
6.000 1.2746 0.01237 0.00613 -0.0857 0.1442 1.0001
6.250 1.2974 0.01276 0.00648 -0.0852 0.1344 1.0001
6.500 1.3200 0.01315 0.00682 -0.0847 0.1257 1.0001
6.750 1.3429 0.01350 0.00716 -0.0842 0.1190 1.0001
7.250 1.3865 0.01429 0.00790 -0.0829 0.1048 1.0001
7.500 1.4073 0.01473 0.00830 -0.0821 0.0987 1.0001
7.750 1.4286 0.01511 0.00868 -0.0814 0.0935 1.0001
8.000 1.4477 0.01558 0.00913 -0.0804 0.0870 1.0001
8.250 1.4666 0.01601 0.00956 -0.0793 0.0816 1.0001
8.500 1.4813 0.01657 0.01008 -0.0775 0.0741 1.0001
8.750 1.4971 0.01710 0.01060 -0.0759 0.0673 1.0001
9.000 1.5070 0.01799 0.01139 -0.0736 0.0534 1.0001
9.250 1.5038 0.01970 0.01292 -0.0696 0.0277 1.0001
9.500 1.5122 0.02077 0.01397 -0.0674 0.0205 1.0001
9.750 1.5233 0.02171 0.01493 -0.0657 0.0172 1.0001
10.000 1.5347 0.02266 0.01590 -0.0641 0.0153 1.0001
10.250 1.5466 0.02361 0.01689 -0.0628 0.0141 1.0001
10.500 1.5572 0.02468 0.01801 -0.0614 0.0130 1.0001
10.750 1.5687 0.02574 0.01911 -0.0602 0.0124 1.0001
11.000 1.5796 0.02687 0.02029 -0.0591 0.0118 1.0001
11.250 1.5892 0.02813 0.02160 -0.0579 0.0113 1.0001
11.500 1.5978 0.02953 0.02305 -0.0568 0.0108 1.0001
11.750 1.6051 0.03109 0.02468 -0.0558 0.0103 1.0001
12.000 1.6123 0.03270 0.02634 -0.0549 0.0099 1.0001
12.250 1.6199 0.03433 0.02804 -0.0541 0.0096 1.0001
12.500 1.6264 0.03611 0.02989 -0.0534 0.0093 1.0001
12.750 1.6316 0.03806 0.03190 -0.0528 0.0090 1.0001
13.000 1.6355 0.04017 0.03408 -0.0522 0.0087 1.0001
13.250 1.6382 0.04249 0.03647 -0.0517 0.0085 1.0001
13.500 1.6394 0.04503 0.03909 -0.0513 0.0082 1.0001
13.750 1.6390 0.04783 0.04197 -0.0510 0.0080 1.0001
14.000 1.6370 0.05089 0.04511 -0.0509 0.0078 1.0001
14.250 1.6369 0.05383 0.04814 -0.0509 0.0077 1.0001
14.500 1.6356 0.05700 0.05140 -0.0511 0.0075 1.0001
14.750 1.6326 0.06044 0.05493 -0.0514 0.0074 1.0001
15.000 1.6286 0.06409 0.05868 -0.0518 0.0073 1.0001
15.250 1.6236 0.06796 0.06265 -0.0524 0.0072 1.0001
15.500 1.6174 0.07208 0.06687 -0.0531 0.0071 1.0001
15.750 1.6095 0.07649 0.07137 -0.0540 0.0070 1.0001
16.000 1.6006 0.08111 0.07610 -0.0550 0.0069 1.0001
16.250 1.5909 0.08593 0.08103 -0.0561 0.0068 1.0001
16.500 1.5799 0.09101 0.08622 -0.0575 0.0067 1.0001
16.750 1.5678 0.09630 0.09161 -0.0589 0.0066 1.0001
17.000 1.5554 0.10171 0.09712 -0.0605 0.0066 1.0001
17.250 1.5429 0.10722 0.10274 -0.0623 0.0065 1.0001
17.500 1.5300 0.11284 0.10846 -0.0641 0.0064 1.0001
17.750 1.5166 0.11857 0.11429 -0.0662 0.0063 1.0001
18.000 1.5033 0.12439 0.12020 -0.0684 0.0063 1.0001
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