NACA M2 (nacam2-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA M2 (nacam2-il) Reynolds number: 500,000 Max Cl/Cd: 54.44 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-nacam2-il-500000-n5.txt Download as CSV file: xf-nacam2-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA M2
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
------ -------- --------- --------- -------- -------- --------
-13.500 -0.9456 0.10000 0.09779 0.0149 1.0000 0.0066
-13.250 -1.0975 0.05672 0.05415 -0.0147 1.0000 0.0056
-13.000 -1.1256 0.04840 0.04557 -0.0208 1.0000 0.0056
-12.750 -1.1456 0.04343 0.04035 -0.0218 1.0000 0.0056
-12.500 -1.1594 0.03998 0.03667 -0.0201 1.0000 0.0057
-12.250 -1.1668 0.03717 0.03361 -0.0177 1.0000 0.0057
-12.000 -1.1657 0.03453 0.03071 -0.0159 1.0000 0.0059
-11.750 -1.1595 0.03221 0.02812 -0.0143 1.0000 0.0060
-11.500 -1.1492 0.03021 0.02586 -0.0129 1.0000 0.0062
-11.250 -1.1357 0.02849 0.02387 -0.0118 1.0000 0.0064
-11.000 -1.1222 0.02666 0.02180 -0.0105 1.0000 0.0067
-10.750 -1.1060 0.02518 0.02016 -0.0095 1.0000 0.0070
-10.500 -1.0868 0.02407 0.01891 -0.0087 1.0000 0.0074
-10.250 -1.0668 0.02301 0.01771 -0.0080 1.0000 0.0077
-10.000 -1.0462 0.02196 0.01650 -0.0072 1.0000 0.0081
-9.750 -1.0252 0.02093 0.01531 -0.0065 1.0000 0.0085
-9.500 -1.0036 0.01995 0.01417 -0.0058 1.0000 0.0089
-9.250 -0.9813 0.01907 0.01313 -0.0052 1.0000 0.0093
-9.000 -0.9593 0.01810 0.01204 -0.0045 1.0000 0.0102
-8.750 -0.9352 0.01756 0.01146 -0.0042 1.0000 0.0111
-8.500 -0.9107 0.01706 0.01089 -0.0038 1.0000 0.0121
-8.250 -0.8864 0.01649 0.01021 -0.0034 1.0000 0.0130
-8.000 -0.8623 0.01584 0.00951 -0.0029 1.0000 0.0143
-7.750 -0.8367 0.01554 0.00921 -0.0027 1.0000 0.0157
-7.500 -0.8110 0.01524 0.00887 -0.0024 1.0000 0.0173
-7.250 -0.7852 0.01497 0.00851 -0.0021 1.0000 0.0189
-7.000 -0.7598 0.01459 0.00807 -0.0018 1.0000 0.0200
-6.750 -0.7350 0.01408 0.00754 -0.0014 1.0000 0.0218
-6.500 -0.7092 0.01381 0.00725 -0.0012 1.0000 0.0234
-6.250 -0.6835 0.01352 0.00692 -0.0009 1.0000 0.0251
-6.000 -0.6580 0.01319 0.00653 -0.0005 1.0000 0.0266
-5.750 -0.6324 0.01292 0.00621 -0.0002 1.0000 0.0277
-5.500 -0.6067 0.01268 0.00593 0.0002 1.0000 0.0283
-5.250 -0.5826 0.01212 0.00532 0.0008 1.0000 0.0295
-5.000 -0.5586 0.01158 0.00473 0.0015 1.0000 0.0313
-4.750 -0.5342 0.01120 0.00432 0.0021 1.0000 0.0327
-4.500 -0.5096 0.01089 0.00400 0.0027 1.0000 0.0342
-4.250 -0.4851 0.01061 0.00369 0.0033 1.0000 0.0354
-4.000 -0.4606 0.01036 0.00340 0.0039 1.0000 0.0365
-3.750 -0.4361 0.01014 0.00316 0.0046 1.0000 0.0375
-3.500 -0.4118 0.00995 0.00294 0.0053 1.0000 0.0384
-3.250 -0.3796 0.00975 0.00272 0.0042 0.9975 0.0394
-3.000 -0.3452 0.00952 0.00249 0.0027 0.9947 0.0431
-2.750 -0.3119 0.00929 0.00230 0.0014 0.9907 0.0497
-2.500 -0.2785 0.00892 0.00210 0.0000 0.9870 0.0867
-2.250 -0.2469 0.00845 0.00192 -0.0012 0.9818 0.1529
-2.000 -0.2152 0.00795 0.00175 -0.0024 0.9762 0.2372
-1.750 -0.1847 0.00751 0.00162 -0.0032 0.9688 0.3174
-1.500 -0.1542 0.00703 0.00151 -0.0041 0.9609 0.4131
-1.000 -0.0970 0.00631 0.00135 -0.0044 0.9310 0.5705
-0.750 -0.0718 0.00597 0.00131 -0.0037 0.9111 0.6551
-0.500 -0.0471 0.00572 0.00130 -0.0028 0.8927 0.7245
-0.250 -0.0228 0.00557 0.00130 -0.0016 0.8685 0.7787
0.000 0.0000 0.00551 0.00130 0.0000 0.8298 0.8293
0.250 0.0229 0.00557 0.00130 0.0016 0.7800 0.8684
0.500 0.0471 0.00572 0.00130 0.0028 0.7243 0.8927
0.750 0.0717 0.00597 0.00131 0.0037 0.6544 0.9111
1.000 0.0970 0.00631 0.00135 0.0044 0.5715 0.9310
1.250 0.1240 0.00670 0.00142 0.0046 0.4822 0.9490
1.500 0.1541 0.00702 0.00151 0.0041 0.4142 0.9609
1.750 0.1846 0.00752 0.00162 0.0032 0.3159 0.9688
2.000 0.2152 0.00795 0.00175 0.0024 0.2359 0.9762
2.250 0.2469 0.00845 0.00192 0.0012 0.1532 0.9819
2.500 0.2785 0.00892 0.00210 0.0000 0.0866 0.9870
2.750 0.3119 0.00929 0.00230 -0.0014 0.0497 0.9907
3.000 0.3451 0.00952 0.00249 -0.0027 0.0432 0.9947
3.250 0.3795 0.00975 0.00272 -0.0042 0.0394 0.9975
3.500 0.4117 0.00995 0.00294 -0.0053 0.0384 1.0000
3.750 0.4361 0.01014 0.00316 -0.0046 0.0375 1.0000
4.000 0.4605 0.01036 0.00340 -0.0039 0.0365 1.0000
4.250 0.4851 0.01061 0.00369 -0.0033 0.0355 1.0000
4.500 0.5096 0.01089 0.00400 -0.0027 0.0342 1.0000
4.750 0.5341 0.01120 0.00432 -0.0021 0.0327 1.0000
5.000 0.5586 0.01158 0.00473 -0.0015 0.0313 1.0000
5.250 0.5826 0.01212 0.00531 -0.0008 0.0295 1.0000
5.500 0.6067 0.01268 0.00593 -0.0002 0.0283 1.0000
5.750 0.6323 0.01292 0.00621 0.0002 0.0277 1.0000
6.000 0.6580 0.01319 0.00653 0.0005 0.0266 1.0000
6.250 0.6835 0.01352 0.00692 0.0009 0.0251 1.0000
6.500 0.7092 0.01381 0.00725 0.0012 0.0234 1.0000
6.750 0.7350 0.01408 0.00754 0.0014 0.0218 1.0000
7.000 0.7598 0.01459 0.00807 0.0018 0.0200 1.0000
7.250 0.7852 0.01497 0.00851 0.0021 0.0189 1.0000
7.500 0.8110 0.01525 0.00888 0.0024 0.0173 1.0000
7.750 0.8367 0.01554 0.00921 0.0027 0.0157 1.0000
8.000 0.8623 0.01584 0.00951 0.0029 0.0143 1.0000
8.250 0.8864 0.01649 0.01022 0.0034 0.0130 1.0000
8.500 0.9107 0.01706 0.01089 0.0038 0.0121 1.0000
8.750 0.9352 0.01756 0.01145 0.0041 0.0111 1.0000
9.000 0.9594 0.01810 0.01204 0.0045 0.0102 1.0000
9.250 0.9814 0.01907 0.01313 0.0052 0.0093 1.0000
9.500 1.0037 0.01995 0.01417 0.0058 0.0089 1.0000
9.750 1.0253 0.02092 0.01530 0.0065 0.0085 1.0000
10.000 1.0463 0.02195 0.01650 0.0072 0.0081 1.0000
10.250 1.0669 0.02300 0.01770 0.0080 0.0077 1.0000
10.500 1.0870 0.02406 0.01890 0.0087 0.0074 1.0000
10.750 1.1062 0.02517 0.02015 0.0095 0.0070 1.0000
11.000 1.1223 0.02667 0.02181 0.0105 0.0067 1.0000
11.250 1.1360 0.02848 0.02385 0.0117 0.0064 1.0000
11.500 1.1494 0.03021 0.02586 0.0129 0.0062 1.0000
11.750 1.1598 0.03221 0.02812 0.0143 0.0060 1.0000
12.000 1.1660 0.03454 0.03071 0.0158 0.0059 1.0000
12.250 1.1672 0.03717 0.03361 0.0176 0.0057 1.0000
12.500 1.1598 0.04000 0.03669 0.0200 0.0057 1.0000
12.750 1.1460 0.04346 0.04038 0.0217 0.0056 1.0000
13.000 1.1266 0.04837 0.04554 0.0207 0.0056 1.0000
13.250 1.0976 0.05688 0.05432 0.0144 0.0056 1.0000
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