NACA M12 (nacam12-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA M12 (nacam12-il) Reynolds number: 100,000 Max Cl/Cd: 49.38 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-nacam12-il-100000.txt Download as CSV file: xf-nacam12-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4859 0.09675 0.09157 -0.0214 1.0000 0.1310
-9.000 -0.5169 0.09098 0.08592 -0.0301 1.0000 0.1339
-8.750 -0.5772 0.08634 0.08117 -0.0358 1.0000 0.1346
-8.500 -0.5365 0.08165 0.07664 -0.0333 1.0000 0.1359
-8.250 -0.5257 0.07832 0.07333 -0.0322 1.0000 0.1377
-8.000 -0.5285 0.07464 0.06965 -0.0325 1.0000 0.1403
-7.750 -0.5444 0.07056 0.06549 -0.0332 1.0000 0.1435
-7.500 -0.5872 0.06784 0.06224 -0.0316 1.0000 0.1454
-7.250 -0.5657 0.06298 0.05767 -0.0308 1.0000 0.1468
-7.000 -0.5603 0.05992 0.05462 -0.0289 1.0000 0.1482
-6.750 -0.5605 0.05702 0.05164 -0.0266 1.0000 0.1496
-6.500 -0.5619 0.05422 0.04871 -0.0240 1.0000 0.1508
-6.250 -0.5628 0.05150 0.04582 -0.0213 1.0000 0.1519
-6.000 -0.5706 0.04433 0.03710 -0.0164 1.0000 0.1014
-5.750 -0.5587 0.04156 0.03433 -0.0147 1.0000 0.0999
-5.500 -0.5484 0.03932 0.03187 -0.0125 1.0000 0.0993
-5.250 -0.5364 0.03723 0.02951 -0.0105 1.0000 0.0989
-5.000 -0.5224 0.03519 0.02720 -0.0086 1.0000 0.0980
-4.750 -0.5067 0.03326 0.02497 -0.0070 1.0000 0.0970
-4.500 -0.4892 0.03155 0.02296 -0.0056 1.0000 0.0968
-4.250 -0.4704 0.03009 0.02121 -0.0043 1.0000 0.0973
-4.000 -0.4458 0.02884 0.01963 -0.0041 0.9988 0.0997
-3.750 -0.4016 0.02771 0.01832 -0.0077 0.9925 0.1039
-3.500 -0.3581 0.02668 0.01708 -0.0109 0.9852 0.1086
-3.250 -0.3150 0.02572 0.01592 -0.0140 0.9779 0.1149
-3.000 -0.2703 0.02501 0.01507 -0.0175 0.9705 0.1277
-2.750 -0.2306 0.02368 0.01357 -0.0199 0.9624 0.1484
-2.500 -0.1912 0.02044 0.01087 -0.0226 0.9579 0.1870
-2.000 -0.1142 0.01842 0.00993 -0.0279 0.9413 0.3381
-1.750 -0.0822 0.01710 0.00987 -0.0290 0.9327 0.5747
-1.500 -0.0333 0.01677 0.01043 -0.0309 0.9270 0.8410
-1.250 0.0302 0.01691 0.01050 -0.0368 0.9226 0.9055
-1.000 0.0760 0.01702 0.01049 -0.0400 0.9117 0.9268
-0.750 0.1329 0.01693 0.01028 -0.0451 0.9055 0.9422
-0.500 0.1773 0.01697 0.01023 -0.0481 0.8933 0.9559
-0.250 0.2292 0.01688 0.01007 -0.0524 0.8837 0.9681
0.000 0.2775 0.01670 0.00980 -0.0560 0.8731 0.9750
0.250 0.3163 0.01665 0.00970 -0.0580 0.8594 0.9833
0.500 0.3581 0.01654 0.00954 -0.0605 0.8462 0.9908
0.750 0.3989 0.01640 0.00935 -0.0627 0.8332 0.9978
1.000 0.4275 0.01630 0.00918 -0.0624 0.8203 1.0000
1.250 0.4489 0.01634 0.00918 -0.0609 0.8052 1.0000
1.500 0.4704 0.01641 0.00920 -0.0594 0.7902 1.0000
1.750 0.4921 0.01648 0.00924 -0.0580 0.7756 1.0000
2.000 0.5141 0.01656 0.00928 -0.0566 0.7615 1.0000
2.250 0.5365 0.01664 0.00931 -0.0552 0.7478 1.0000
2.500 0.5596 0.01668 0.00930 -0.0538 0.7349 1.0000
2.750 0.5822 0.01677 0.00935 -0.0525 0.7210 1.0000
3.000 0.6042 0.01692 0.00949 -0.0512 0.7062 1.0000
3.250 0.6264 0.01706 0.00962 -0.0498 0.6915 1.0000
3.500 0.6487 0.01719 0.00973 -0.0485 0.6767 1.0000
3.750 0.6713 0.01731 0.00983 -0.0471 0.6618 1.0000
4.000 0.6939 0.01742 0.00991 -0.0458 0.6470 1.0000
4.250 0.7169 0.01754 0.01000 -0.0444 0.6323 1.0000
4.500 0.7401 0.01767 0.01010 -0.0432 0.6178 1.0000
4.750 0.7635 0.01780 0.01020 -0.0420 0.6032 1.0000
5.000 0.7857 0.01800 0.01041 -0.0407 0.5874 1.0000
5.250 0.8080 0.01819 0.01060 -0.0393 0.5713 1.0000
5.500 0.8304 0.01840 0.01081 -0.0380 0.5547 1.0000
5.750 0.8526 0.01855 0.01093 -0.0366 0.5366 1.0000
6.000 0.8721 0.01867 0.01107 -0.0347 0.5135 1.0000
6.250 0.8925 0.01869 0.01101 -0.0328 0.4896 1.0000
6.500 0.9114 0.01884 0.01116 -0.0309 0.4649 1.0000
6.750 0.9306 0.01903 0.01131 -0.0291 0.4410 1.0000
7.000 0.9488 0.01928 0.01156 -0.0272 0.4154 1.0000
7.250 0.9663 0.01957 0.01179 -0.0252 0.3885 1.0000
7.500 0.9822 0.01994 0.01214 -0.0230 0.3575 1.0000
7.750 0.9963 0.02044 0.01258 -0.0206 0.3211 1.0000
8.000 1.0071 0.02118 0.01313 -0.0178 0.2778 1.0000
8.250 1.0132 0.02238 0.01402 -0.0146 0.2253 1.0000
8.500 1.0159 0.02406 0.01529 -0.0110 0.1801 1.0000
8.750 1.0215 0.02574 0.01663 -0.0079 0.1531 1.0000
9.000 1.0324 0.02719 0.01799 -0.0055 0.1356 1.0000
9.250 1.0455 0.02864 0.01928 -0.0036 0.1235 1.0000
9.500 1.0613 0.02992 0.02058 -0.0020 0.1141 1.0000
9.750 1.0799 0.03148 0.02214 -0.0008 0.1067 1.0000
10.000 1.0982 0.03287 0.02349 0.0003 0.1000 1.0000
10.250 1.1214 0.03478 0.02542 0.0007 0.0947 1.0000
10.500 1.1387 0.03631 0.02711 0.0020 0.0897 1.0000
10.750 1.1667 0.03868 0.02930 0.0014 0.0848 1.0000
11.000 1.1801 0.04062 0.03159 0.0031 0.0821 1.0000
11.250 1.1924 0.04255 0.03378 0.0048 0.0788 1.0000
11.500 1.2056 0.04451 0.03587 0.0062 0.0758 1.0000
11.750 1.2270 0.04762 0.03898 0.0062 0.0732 1.0000
12.000 1.2292 0.05067 0.04239 0.0085 0.0718 1.0000
12.250 1.2223 0.05309 0.04521 0.0119 0.0708 1.0000
12.500 1.2107 0.05566 0.04811 0.0156 0.0699 1.0000
12.750 1.1969 0.05857 0.05133 0.0186 0.0691 1.0000
13.000 1.1807 0.06191 0.05496 0.0209 0.0686 1.0000
13.250 1.1615 0.06579 0.05912 0.0224 0.0684 1.0000
13.500 1.1385 0.07032 0.06393 0.0231 0.0684 1.0000
13.750 1.1117 0.07566 0.06953 0.0226 0.0688 1.0000
14.000 1.0812 0.08196 0.07607 0.0208 0.0693 1.0000
14.250 1.0478 0.08940 0.08370 0.0176 0.0700 1.0000
14.500 1.0133 0.09803 0.09251 0.0132 0.0709 1.0000
14.750 0.9812 0.10744 0.10204 0.0082 0.0718 1.0000
15.000 0.9574 0.11661 0.11127 0.0038 0.0726 1.0000
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Polar data table (+)
Polar graphs
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