NACA M2 (nacam2-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA M2 (nacam2-il) Reynolds number: 1,000,000 Max Cl/Cd: 60.31 at α=8° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-nacam2-il-1000000.txt Download as CSV file: xf-nacam2-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.250 -0.8628 0.09065 0.08906 -0.0008 1.0000 0.0087
-14.000 -0.8415 0.09146 0.08990 -0.0002 1.0000 0.0089
-13.750 -1.0758 0.07369 0.07197 0.0009 1.0000 0.0078
-13.500 -1.1449 0.05148 0.04936 -0.0186 1.0000 0.0075
-13.250 -1.1721 0.04449 0.04212 -0.0225 1.0000 0.0075
-13.000 -1.1915 0.04013 0.03753 -0.0222 1.0000 0.0075
-12.750 -1.2045 0.03713 0.03431 -0.0197 1.0000 0.0076
-12.500 -1.2093 0.03448 0.03144 -0.0172 1.0000 0.0077
-12.250 -1.2050 0.03221 0.02895 -0.0154 1.0000 0.0078
-12.000 -1.1953 0.03037 0.02690 -0.0140 1.0000 0.0079
-11.750 -1.1815 0.02890 0.02526 -0.0128 1.0000 0.0080
-11.500 -1.1821 0.02506 0.02096 -0.0103 1.0000 0.0084
-11.250 -1.1678 0.02331 0.01902 -0.0090 1.0000 0.0087
-11.000 -1.1472 0.02247 0.01809 -0.0083 1.0000 0.0091
-10.750 -1.1248 0.02189 0.01746 -0.0078 1.0000 0.0094
-10.500 -1.1021 0.02131 0.01680 -0.0073 1.0000 0.0098
-10.250 -1.0797 0.02060 0.01599 -0.0068 1.0000 0.0102
-10.000 -1.0574 0.01980 0.01507 -0.0062 1.0000 0.0106
-9.750 -1.0345 0.01908 0.01423 -0.0057 1.0000 0.0109
-9.500 -1.0150 0.01758 0.01253 -0.0046 1.0000 0.0114
-9.250 -0.9925 0.01672 0.01160 -0.0041 1.0000 0.0122
-9.000 -0.9672 0.01640 0.01125 -0.0038 1.0000 0.0127
-8.750 -0.9418 0.01606 0.01087 -0.0036 1.0000 0.0133
-8.500 -0.9166 0.01563 0.01039 -0.0032 1.0000 0.0140
-8.250 -0.8910 0.01528 0.00997 -0.0030 1.0000 0.0146
-8.000 -0.8678 0.01439 0.00898 -0.0024 1.0000 0.0156
-7.750 -0.8419 0.01411 0.00870 -0.0022 1.0000 0.0165
-7.500 -0.8155 0.01393 0.00852 -0.0020 1.0000 0.0174
-7.250 -0.7894 0.01366 0.00822 -0.0018 1.0000 0.0184
-7.000 -0.7631 0.01342 0.00794 -0.0016 1.0000 0.0192
-6.750 -0.7362 0.01334 0.00782 -0.0014 1.0000 0.0198
-6.500 -0.7139 0.01218 0.00661 -0.0007 1.0000 0.0216
-6.250 -0.6878 0.01196 0.00639 -0.0004 1.0000 0.0228
-6.000 -0.6619 0.01167 0.00609 -0.0001 1.0000 0.0240
-5.750 -0.6363 0.01137 0.00576 0.0003 1.0000 0.0251
-5.500 -0.6105 0.01117 0.00554 0.0007 1.0000 0.0260
-5.250 -0.5849 0.01100 0.00535 0.0011 1.0000 0.0266
-5.000 -0.5630 0.01004 0.00431 0.0021 1.0000 0.0287
-4.750 -0.5388 0.00967 0.00393 0.0028 1.0000 0.0300
-4.500 -0.5144 0.00941 0.00366 0.0035 1.0000 0.0315
-4.250 -0.4903 0.00916 0.00339 0.0042 1.0000 0.0327
-4.000 -0.4663 0.00893 0.00314 0.0050 1.0000 0.0337
-3.750 -0.4425 0.00874 0.00293 0.0058 1.0000 0.0346
-3.500 -0.4188 0.00858 0.00277 0.0066 1.0000 0.0351
-3.250 -0.3906 0.00830 0.00244 0.0065 0.9993 0.0370
-3.000 -0.3559 0.00803 0.00219 0.0049 0.9975 0.0409
-2.750 -0.3208 0.00782 0.00199 0.0033 0.9957 0.0454
-2.500 -0.2863 0.00730 0.00177 0.0015 0.9942 0.1111
-2.250 -0.2542 0.00664 0.00157 0.0002 0.9911 0.2229
-2.000 -0.2203 0.00606 0.00141 -0.0015 0.9880 0.3344
-1.750 -0.1853 0.00548 0.00127 -0.0034 0.9839 0.4546
-1.500 -0.1545 0.00510 0.00119 -0.0042 0.9752 0.5375
-1.250 -0.1244 0.00482 0.00113 -0.0047 0.9668 0.6054
-1.000 -0.0972 0.00455 0.00110 -0.0045 0.9560 0.6731
-0.750 -0.0717 0.00434 0.00108 -0.0037 0.9426 0.7315
-0.500 -0.0471 0.00415 0.00108 -0.0027 0.9277 0.7901
-0.250 -0.0231 0.00404 0.00108 -0.0015 0.9056 0.8341
0.000 0.0000 0.00402 0.00106 0.0000 0.8702 0.8702
0.250 0.0231 0.00404 0.00108 0.0015 0.8348 0.9062
0.500 0.0471 0.00415 0.00108 0.0027 0.7901 0.9278
0.750 0.0718 0.00434 0.00108 0.0037 0.7323 0.9425
1.000 0.0972 0.00455 0.00110 0.0045 0.6737 0.9559
1.250 0.1244 0.00482 0.00113 0.0047 0.6057 0.9668
1.500 0.1545 0.00510 0.00119 0.0042 0.5384 0.9752
1.750 0.1853 0.00548 0.00127 0.0034 0.4556 0.9839
2.000 0.2203 0.00606 0.00141 0.0015 0.3346 0.9880
2.250 0.2542 0.00665 0.00157 -0.0002 0.2225 0.9911
2.500 0.2863 0.00729 0.00177 -0.0015 0.1122 0.9942
2.750 0.3208 0.00782 0.00199 -0.0033 0.0454 0.9957
3.000 0.3559 0.00803 0.00218 -0.0049 0.0409 0.9976
3.250 0.3906 0.00829 0.00244 -0.0065 0.0371 0.9994
3.500 0.4187 0.00858 0.00277 -0.0066 0.0351 1.0000
3.750 0.4424 0.00874 0.00293 -0.0058 0.0346 1.0000
4.000 0.4662 0.00893 0.00314 -0.0050 0.0337 1.0000
4.250 0.4902 0.00916 0.00339 -0.0042 0.0327 1.0000
4.500 0.5144 0.00941 0.00366 -0.0035 0.0315 1.0000
4.750 0.5387 0.00967 0.00393 -0.0028 0.0300 1.0000
5.000 0.5630 0.01004 0.00431 -0.0021 0.0287 1.0000
5.250 0.5849 0.01100 0.00535 -0.0011 0.0266 1.0000
5.500 0.6104 0.01117 0.00554 -0.0006 0.0260 1.0000
5.750 0.6363 0.01137 0.00576 -0.0003 0.0251 1.0000
6.000 0.6619 0.01166 0.00608 0.0001 0.0240 1.0000
6.250 0.6878 0.01195 0.00639 0.0004 0.0228 1.0000
6.500 0.7139 0.01219 0.00661 0.0007 0.0216 1.0000
6.750 0.7362 0.01334 0.00782 0.0014 0.0198 1.0000
7.000 0.7631 0.01341 0.00793 0.0016 0.0192 1.0000
7.250 0.7894 0.01365 0.00822 0.0018 0.0183 1.0000
7.500 0.8155 0.01393 0.00852 0.0020 0.0174 1.0000
7.750 0.8420 0.01410 0.00870 0.0022 0.0165 1.0000
8.000 0.8678 0.01439 0.00899 0.0024 0.0156 1.0000
8.250 0.8910 0.01529 0.00998 0.0030 0.0146 1.0000
8.500 0.9166 0.01563 0.01039 0.0032 0.0140 1.0000
8.750 0.9418 0.01605 0.01087 0.0035 0.0133 1.0000
9.000 0.9672 0.01640 0.01125 0.0038 0.0127 1.0000
9.250 0.9926 0.01671 0.01159 0.0040 0.0121 1.0000
9.500 1.0151 0.01760 0.01254 0.0046 0.0114 1.0000
9.750 1.0345 0.01910 0.01425 0.0056 0.0109 1.0000
10.000 1.0575 0.01981 0.01508 0.0062 0.0106 1.0000
10.250 1.0799 0.02060 0.01599 0.0068 0.0102 1.0000
10.500 1.1024 0.02130 0.01678 0.0073 0.0098 1.0000
10.750 1.1251 0.02187 0.01744 0.0078 0.0094 1.0000
11.000 1.1474 0.02246 0.01809 0.0083 0.0091 1.0000
11.250 1.1679 0.02332 0.01903 0.0089 0.0087 1.0000
11.500 1.1823 0.02507 0.02096 0.0102 0.0084 1.0000
11.750 1.1820 0.02888 0.02524 0.0127 0.0080 1.0000
12.000 1.1959 0.03034 0.02687 0.0139 0.0079 1.0000
12.250 1.2054 0.03221 0.02895 0.0153 0.0078 1.0000
12.500 1.2099 0.03447 0.03143 0.0171 0.0076 1.0000
12.750 1.2054 0.03711 0.03429 0.0195 0.0075 1.0000
13.000 1.1919 0.04019 0.03759 0.0221 0.0075 1.0000
13.250 1.1735 0.04443 0.04206 0.0224 0.0074 1.0000
13.500 1.1460 0.05149 0.04937 0.0184 0.0075 1.0000
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Polar data table (+)
Polar graphs
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