NACA M2 AIRFOIL (m2-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA M2 AIRFOIL (m2-il) Reynolds number: 1,000,000 Max Cl/Cd: 60.59 at α=8° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-m2-il-1000000.txt Download as CSV file: xf-m2-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: NACA M2 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-13.500 -1.1523 0.05335 0.05139 -0.0155 1.0000 0.0075
-13.250 -1.1847 0.04573 0.04351 -0.0194 1.0000 0.0075
-13.000 -1.2064 0.04120 0.03873 -0.0185 1.0000 0.0075
-12.750 -1.2207 0.03792 0.03523 -0.0157 1.0000 0.0076
-12.500 -1.2226 0.03500 0.03205 -0.0139 1.0000 0.0077
-12.250 -1.2172 0.03259 0.02941 -0.0123 1.0000 0.0078
-12.000 -1.2066 0.03065 0.02726 -0.0111 1.0000 0.0079
-11.750 -1.1921 0.02911 0.02554 -0.0101 1.0000 0.0081
-11.500 -1.1892 0.02551 0.02150 -0.0080 1.0000 0.0084
-11.250 -1.1755 0.02347 0.01925 -0.0068 1.0000 0.0088
-11.000 -1.1547 0.02255 0.01824 -0.0062 1.0000 0.0091
-10.750 -1.1320 0.02192 0.01754 -0.0058 1.0000 0.0094
-10.500 -1.1086 0.02135 0.01689 -0.0055 1.0000 0.0098
-10.250 -1.0857 0.02062 0.01606 -0.0050 1.0000 0.0103
-10.000 -1.0627 0.01983 0.01515 -0.0046 1.0000 0.0107
-9.750 -1.0391 0.01910 0.01430 -0.0042 1.0000 0.0110
-9.500 -1.0188 0.01760 0.01259 -0.0034 1.0000 0.0115
-9.250 -0.9956 0.01673 0.01165 -0.0030 1.0000 0.0123
-9.000 -0.9697 0.01640 0.01130 -0.0029 1.0000 0.0128
-8.750 -0.9439 0.01604 0.01090 -0.0027 1.0000 0.0135
-8.500 -0.9182 0.01562 0.01041 -0.0025 1.0000 0.0142
-8.250 -0.8919 0.01528 0.01001 -0.0024 1.0000 0.0148
-8.000 -0.8681 0.01434 0.00898 -0.0020 1.0000 0.0158
-7.750 -0.8417 0.01406 0.00871 -0.0020 1.0000 0.0167
-7.500 -0.8148 0.01385 0.00849 -0.0019 1.0000 0.0176
-7.250 -0.7882 0.01355 0.00815 -0.0019 1.0000 0.0187
-7.000 -0.7612 0.01333 0.00789 -0.0018 1.0000 0.0195
-6.750 -0.7336 0.01328 0.00781 -0.0018 1.0000 0.0200
-6.500 -0.7106 0.01203 0.00649 -0.0013 1.0000 0.0220
-6.250 -0.6840 0.01176 0.00623 -0.0012 1.0000 0.0233
-6.000 -0.6576 0.01144 0.00588 -0.0010 1.0000 0.0245
-5.750 -0.6315 0.01113 0.00554 -0.0008 1.0000 0.0256
-5.500 -0.6053 0.01095 0.00534 -0.0005 1.0000 0.0264
-5.250 -0.5810 0.01050 0.00485 0.0001 1.0000 0.0273
-5.000 -0.5583 0.00983 0.00411 0.0010 1.0000 0.0292
-4.750 -0.5347 0.00948 0.00374 0.0017 1.0000 0.0306
-4.500 -0.5109 0.00922 0.00347 0.0025 1.0000 0.0321
-4.250 -0.4871 0.00897 0.00320 0.0033 1.0000 0.0332
-4.000 -0.4632 0.00876 0.00297 0.0040 1.0000 0.0342
-3.750 -0.4300 0.00855 0.00273 0.0028 0.9985 0.0352
-3.500 -0.3955 0.00828 0.00244 0.0012 0.9967 0.0369
-3.250 -0.3597 0.00801 0.00218 -0.0006 0.9950 0.0413
-3.000 -0.3232 0.00769 0.00196 -0.0026 0.9928 0.0589
-2.750 -0.2898 0.00744 0.00188 -0.0039 0.9898 0.0923
-2.500 -0.2552 0.00731 0.00179 -0.0055 0.9855 0.1024
-2.250 -0.2238 0.00721 0.00171 -0.0062 0.9780 0.1093
-2.000 -0.1956 0.00711 0.00164 -0.0061 0.9705 0.1178
-1.750 -0.1699 0.00701 0.00157 -0.0055 0.9622 0.1256
-1.500 -0.1449 0.00685 0.00150 -0.0048 0.9534 0.1471
-1.250 -0.1229 0.00593 0.00129 -0.0040 0.9425 0.3616
-1.000 -0.0979 0.00549 0.00120 -0.0035 0.9302 0.4623
-0.750 -0.0731 0.00508 0.00113 -0.0028 0.9138 0.5592
-0.500 -0.0490 0.00476 0.00104 -0.0019 0.8800 0.6437
-0.250 -0.0250 0.00462 0.00098 -0.0008 0.8326 0.7142
0.000 0.0000 0.00458 0.00097 0.0000 0.7811 0.7798
0.250 0.0250 0.00462 0.00098 0.0008 0.7137 0.8326
0.500 0.0491 0.00476 0.00104 0.0018 0.6444 0.8798
0.750 0.0731 0.00508 0.00113 0.0028 0.5589 0.9137
1.000 0.0979 0.00549 0.00120 0.0034 0.4623 0.9301
1.250 0.1230 0.00591 0.00129 0.0040 0.3646 0.9425
1.500 0.1449 0.00685 0.00150 0.0048 0.1473 0.9536
1.750 0.1699 0.00701 0.00157 0.0055 0.1256 0.9622
2.000 0.1956 0.00711 0.00164 0.0061 0.1178 0.9706
2.250 0.2238 0.00721 0.00171 0.0062 0.1093 0.9781
2.500 0.2551 0.00731 0.00179 0.0055 0.1024 0.9855
2.750 0.2899 0.00744 0.00188 0.0039 0.0923 0.9898
3.000 0.3233 0.00769 0.00196 0.0026 0.0589 0.9928
3.250 0.3598 0.00801 0.00218 0.0006 0.0413 0.9950
3.500 0.3955 0.00828 0.00244 -0.0012 0.0369 0.9967
3.750 0.4300 0.00855 0.00273 -0.0028 0.0352 0.9985
4.000 0.4631 0.00876 0.00297 -0.0040 0.0342 1.0000
4.250 0.4870 0.00897 0.00320 -0.0033 0.0332 1.0000
4.500 0.5108 0.00922 0.00347 -0.0025 0.0321 1.0000
4.750 0.5346 0.00948 0.00375 -0.0017 0.0306 1.0000
5.000 0.5582 0.00983 0.00411 -0.0010 0.0291 1.0000
5.250 0.5810 0.01049 0.00483 -0.0001 0.0274 1.0000
5.500 0.6053 0.01096 0.00535 0.0005 0.0264 1.0000
5.750 0.6314 0.01113 0.00554 0.0008 0.0256 1.0000
6.000 0.6576 0.01144 0.00588 0.0010 0.0245 1.0000
6.250 0.6840 0.01176 0.00622 0.0012 0.0232 1.0000
6.500 0.7106 0.01204 0.00650 0.0013 0.0220 1.0000
6.750 0.7337 0.01328 0.00781 0.0018 0.0200 1.0000
7.000 0.7612 0.01333 0.00789 0.0018 0.0195 1.0000
7.250 0.7882 0.01357 0.00817 0.0019 0.0187 1.0000
7.500 0.8149 0.01385 0.00849 0.0019 0.0176 1.0000
7.750 0.8417 0.01407 0.00871 0.0020 0.0167 1.0000
8.000 0.8682 0.01433 0.00897 0.0020 0.0158 1.0000
8.250 0.8920 0.01529 0.01003 0.0024 0.0148 1.0000
8.500 0.9183 0.01561 0.01041 0.0025 0.0142 1.0000
8.750 0.9440 0.01604 0.01089 0.0027 0.0135 1.0000
9.000 0.9698 0.01640 0.01130 0.0029 0.0128 1.0000
9.250 0.9956 0.01674 0.01165 0.0030 0.0123 1.0000
9.500 1.0188 0.01761 0.01260 0.0034 0.0115 1.0000
9.750 1.0392 0.01910 0.01430 0.0042 0.0110 1.0000
10.000 1.0629 0.01982 0.01513 0.0046 0.0107 1.0000
10.250 1.0858 0.02061 0.01605 0.0050 0.0103 1.0000
10.500 1.1089 0.02133 0.01687 0.0054 0.0098 1.0000
10.750 1.1321 0.02191 0.01753 0.0058 0.0094 1.0000
11.000 1.1549 0.02254 0.01822 0.0062 0.0091 1.0000
11.250 1.1757 0.02346 0.01923 0.0067 0.0088 1.0000
11.500 1.1892 0.02554 0.02154 0.0080 0.0084 1.0000
11.750 1.1928 0.02904 0.02546 0.0100 0.0081 1.0000
12.000 1.2073 0.03059 0.02720 0.0110 0.0079 1.0000
12.250 1.2176 0.03258 0.02940 0.0123 0.0078 1.0000
12.500 1.2229 0.03501 0.03206 0.0138 0.0077 1.0000
12.750 1.2213 0.03791 0.03522 0.0156 0.0075 1.0000
13.000 1.2079 0.04112 0.03865 0.0183 0.0075 1.0000
13.250 1.1869 0.04558 0.04335 0.0193 0.0075 1.0000
13.500 1.1548 0.05310 0.05113 0.0156 0.0075 1.0000
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