NACA M12 (nacam12-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA M12 (nacam12-il) Reynolds number: 50,000 Max Cl/Cd: 31.79 at α=8.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-nacam12-il-50000.txt Download as CSV file: xf-nacam12-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: NACA M12
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.4510 0.10639 0.09909 -0.0045 1.0000 0.3144
-8.750 -0.4539 0.10393 0.09670 -0.0041 1.0000 0.3321
-8.500 -0.4622 0.10181 0.09467 -0.0036 1.0000 0.3497
-8.250 -0.4248 0.09698 0.08978 -0.0014 1.0000 0.3739
-8.000 -0.4332 0.09529 0.08819 0.0000 1.0000 0.3991
-7.750 -0.4088 0.09175 0.08463 0.0021 1.0000 0.4300
-7.500 -0.3932 0.08885 0.08174 0.0042 1.0000 0.4625
-7.250 -0.3788 0.08608 0.07900 0.0063 1.0000 0.4965
-7.000 -0.3618 0.08309 0.07602 0.0080 1.0000 0.5293
-6.750 -0.3524 0.08025 0.07322 0.0095 1.0000 0.5559
-5.750 -0.5451 0.05131 0.04376 -0.0177 1.0000 0.2224
-5.500 -0.5423 0.04580 0.03721 -0.0171 1.0000 0.1918
-5.250 -0.5282 0.04311 0.03426 -0.0155 1.0000 0.1855
-5.000 -0.5143 0.04082 0.03124 -0.0136 1.0000 0.1772
-4.750 -0.4974 0.03852 0.02869 -0.0122 1.0000 0.1738
-4.500 -0.4796 0.03665 0.02632 -0.0106 1.0000 0.1700
-4.250 -0.4605 0.03510 0.02429 -0.0092 1.0000 0.1686
-4.000 -0.4404 0.03330 0.02228 -0.0081 1.0000 0.1710
-3.750 -0.4197 0.03182 0.02049 -0.0071 1.0000 0.1759
-3.500 -0.3971 0.03020 0.01865 -0.0064 1.0000 0.1808
-3.250 -0.3723 0.02869 0.01705 -0.0059 1.0000 0.1870
-3.000 -0.3449 0.02712 0.01555 -0.0057 1.0000 0.1991
-2.750 -0.3166 0.02584 0.01453 -0.0057 1.0000 0.2188
-2.500 -0.2953 0.02518 0.01417 -0.0049 1.0000 0.2483
-2.250 -0.2751 0.02468 0.01391 -0.0039 1.0000 0.3042
-2.000 -0.1327 0.02250 0.01449 -0.0194 1.0000 1.0000
-1.750 -0.1317 0.02270 0.01447 -0.0161 1.0000 1.0000
-1.500 -0.1288 0.02295 0.01452 -0.0132 1.0000 1.0000
-1.250 -0.1241 0.02325 0.01463 -0.0106 1.0000 1.0000
-1.000 -0.1181 0.02360 0.01480 -0.0083 1.0000 1.0000
-0.750 -0.1104 0.02400 0.01503 -0.0063 1.0000 1.0000
-0.500 -0.1013 0.02447 0.01534 -0.0046 1.0000 1.0000
-0.250 -0.0651 0.02525 0.01592 -0.0080 0.9923 1.0000
0.000 -0.0139 0.02614 0.01661 -0.0140 0.9777 1.0000
0.250 0.0336 0.02698 0.01730 -0.0192 0.9629 1.0000
0.500 0.0789 0.02777 0.01796 -0.0237 0.9479 1.0000
0.750 0.1226 0.02853 0.01862 -0.0279 0.9330 1.0000
1.000 0.1658 0.02925 0.01926 -0.0318 0.9182 1.0000
1.250 0.2105 0.02993 0.01989 -0.0357 0.9037 1.0000
1.500 0.2517 0.03057 0.02049 -0.0390 0.8889 1.0000
1.750 0.2845 0.03120 0.02111 -0.0406 0.8733 1.0000
2.000 0.3157 0.03187 0.02176 -0.0419 0.8580 1.0000
2.250 0.3468 0.03253 0.02243 -0.0431 0.8427 1.0000
2.500 0.3778 0.03319 0.02311 -0.0442 0.8278 1.0000
2.750 0.4105 0.03382 0.02376 -0.0454 0.8131 1.0000
3.000 0.4462 0.03436 0.02435 -0.0470 0.7987 1.0000
3.250 0.4863 0.03470 0.02476 -0.0488 0.7849 1.0000
3.500 0.5232 0.03499 0.02512 -0.0499 0.7708 1.0000
3.750 0.5453 0.03565 0.02585 -0.0490 0.7551 1.0000
4.000 0.5683 0.03628 0.02653 -0.0481 0.7394 1.0000
4.250 0.5918 0.03687 0.02718 -0.0471 0.7236 1.0000
4.500 0.6167 0.03735 0.02774 -0.0462 0.7076 1.0000
4.750 0.6428 0.03770 0.02820 -0.0452 0.6914 1.0000
5.000 0.6696 0.03795 0.02854 -0.0441 0.6750 1.0000
5.250 0.6971 0.03809 0.02878 -0.0429 0.6584 1.0000
5.500 0.7250 0.03812 0.02893 -0.0415 0.6415 1.0000
5.750 0.7536 0.03803 0.02896 -0.0401 0.6244 1.0000
6.000 0.7841 0.03772 0.02876 -0.0386 0.6068 1.0000
6.250 0.8180 0.03705 0.02823 -0.0371 0.5888 1.0000
6.500 0.8532 0.03615 0.02742 -0.0356 0.5695 1.0000
6.750 0.8680 0.03670 0.02810 -0.0328 0.5462 1.0000
7.000 0.9149 0.03426 0.02564 -0.0311 0.5206 1.0000
7.250 0.9402 0.03323 0.02460 -0.0282 0.4893 1.0000
7.500 0.9665 0.03212 0.02340 -0.0254 0.4555 1.0000
7.750 0.9863 0.03169 0.02288 -0.0224 0.4199 1.0000
8.000 1.0004 0.03167 0.02278 -0.0189 0.3799 1.0000
8.250 1.0130 0.03187 0.02271 -0.0154 0.3348 1.0000
8.500 1.0216 0.03276 0.02321 -0.0116 0.2880 1.0000
8.750 1.0313 0.03425 0.02435 -0.0085 0.2481 1.0000
9.000 1.0441 0.03612 0.02602 -0.0062 0.2189 1.0000
9.250 1.0642 0.03819 0.02782 -0.0050 0.1975 1.0000
9.500 1.0821 0.04036 0.02998 -0.0036 0.1817 1.0000
9.750 1.1019 0.04267 0.03234 -0.0025 0.1698 1.0000
10.000 1.1124 0.04530 0.03534 -0.0005 0.1611 1.0000
10.250 1.1340 0.04796 0.03791 0.0000 0.1527 1.0000
10.500 1.1348 0.05108 0.04157 0.0028 0.1485 1.0000
10.750 1.1425 0.05394 0.04466 0.0046 0.1432 1.0000
11.000 1.1567 0.05720 0.04793 0.0055 0.1380 1.0000
11.250 1.1441 0.06091 0.05211 0.0088 0.1367 1.0000
11.500 1.1271 0.06487 0.05646 0.0118 0.1360 1.0000
11.750 1.1035 0.06890 0.06077 0.0148 0.1359 1.0000
12.000 1.0759 0.07343 0.06553 0.0170 0.1363 1.0000
12.250 1.0461 0.07884 0.07112 0.0175 0.1370 1.0000
12.500 1.0164 0.08520 0.07762 0.0166 0.1379 1.0000
12.750 0.9898 0.09235 0.08486 0.0145 0.1388 1.0000
13.000 0.8227 0.12994 0.12236 -0.0112 0.1686 1.0000
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Polar data table (+)
Polar graphs
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