NACA M2 (nacam2-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA M2 (nacam2-il) Reynolds number: 50,000 Max Cl/Cd: 25.47 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-nacam2-il-50000.txt Download as CSV file: xf-nacam2-il-50000.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 = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.6229 0.09629 0.08926 0.0330 1.0000 0.3905
-7.250 -0.7309 0.06212 0.05440 -0.0107 1.0000 0.1674
-7.000 -0.7197 0.05554 0.04740 -0.0116 1.0000 0.1518
-6.750 -0.7109 0.04978 0.04065 -0.0116 1.0000 0.1393
-6.500 -0.6917 0.04542 0.03608 -0.0111 1.0000 0.1370
-6.250 -0.6738 0.04179 0.03188 -0.0103 1.0000 0.1375
-6.000 -0.6537 0.03864 0.02805 -0.0093 1.0000 0.1390
-5.750 -0.6304 0.03554 0.02450 -0.0084 1.0000 0.1396
-5.500 -0.6056 0.03267 0.02143 -0.0078 1.0000 0.1421
-5.250 -0.5806 0.03060 0.01914 -0.0071 1.0000 0.1497
-5.000 -0.5544 0.02848 0.01674 -0.0063 1.0000 0.1568
-4.750 -0.5266 0.02660 0.01470 -0.0056 1.0000 0.1650
-4.500 -0.4987 0.02481 0.01294 -0.0049 1.0000 0.1777
-4.250 -0.4722 0.02319 0.01147 -0.0041 1.0000 0.2032
-4.000 -0.4468 0.02111 0.00982 -0.0031 1.0000 0.2594
-3.750 -0.4476 0.01757 0.00910 0.0046 1.0000 0.6406
-3.500 -0.4223 0.01833 0.01018 0.0123 1.0000 0.8446
-3.250 -0.2112 0.02032 0.01065 -0.0146 1.0000 1.0000
-3.000 -0.1958 0.01947 0.00962 -0.0147 1.0000 1.0000
-2.750 -0.1796 0.01877 0.00874 -0.0145 1.0000 1.0000
-2.500 -0.1629 0.01819 0.00802 -0.0141 1.0000 1.0000
-2.250 -0.1458 0.01771 0.00740 -0.0134 1.0000 1.0000
-2.000 -0.1286 0.01731 0.00689 -0.0126 1.0000 1.0000
-1.750 -0.1114 0.01697 0.00646 -0.0115 1.0000 1.0000
-1.500 -0.0944 0.01670 0.00609 -0.0103 1.0000 1.0000
-1.250 -0.0776 0.01647 0.00580 -0.0090 1.0000 1.0000
-1.000 -0.0613 0.01629 0.00557 -0.0074 1.0000 1.0000
-0.750 -0.0454 0.01616 0.00540 -0.0057 1.0000 1.0000
-0.500 -0.0300 0.01606 0.00528 -0.0039 1.0000 1.0000
-0.250 -0.0149 0.01601 0.00521 -0.0020 1.0000 1.0000
0.000 0.0000 0.01599 0.00518 0.0000 1.0000 1.0000
0.250 0.0149 0.01601 0.00521 0.0020 1.0000 1.0000
0.500 0.0300 0.01606 0.00528 0.0039 1.0000 1.0000
0.750 0.0454 0.01616 0.00540 0.0057 1.0000 1.0000
1.000 0.0613 0.01629 0.00557 0.0074 1.0000 1.0000
1.250 0.0777 0.01647 0.00580 0.0090 1.0000 1.0000
1.500 0.0944 0.01670 0.00609 0.0103 1.0000 1.0000
1.750 0.1115 0.01697 0.00646 0.0115 1.0000 1.0000
2.000 0.1287 0.01731 0.00689 0.0126 1.0000 1.0000
2.250 0.1459 0.01771 0.00740 0.0134 1.0000 1.0000
2.500 0.1630 0.01819 0.00801 0.0141 1.0000 1.0000
2.750 0.1797 0.01877 0.00873 0.0145 1.0000 1.0000
3.000 0.1959 0.01946 0.00961 0.0147 1.0000 1.0000
3.250 0.2114 0.02031 0.01064 0.0146 1.0000 1.0000
3.500 0.4223 0.01833 0.01018 -0.0123 0.8446 1.0000
3.750 0.4475 0.01757 0.00910 -0.0046 0.6405 1.0000
4.000 0.4468 0.02111 0.00982 0.0031 0.2594 1.0000
4.250 0.4722 0.02319 0.01147 0.0041 0.2032 1.0000
4.500 0.4987 0.02481 0.01294 0.0049 0.1777 1.0000
4.750 0.5266 0.02660 0.01470 0.0056 0.1650 1.0000
5.000 0.5543 0.02848 0.01674 0.0063 0.1568 1.0000
5.250 0.5806 0.03060 0.01914 0.0071 0.1497 1.0000
5.500 0.6056 0.03267 0.02143 0.0078 0.1421 1.0000
5.750 0.6304 0.03554 0.02450 0.0084 0.1396 1.0000
6.000 0.6537 0.03864 0.02806 0.0093 0.1390 1.0000
6.250 0.6738 0.04179 0.03188 0.0103 0.1375 1.0000
6.500 0.6917 0.04543 0.03608 0.0111 0.1370 1.0000
6.750 0.7110 0.04978 0.04065 0.0116 0.1393 1.0000
7.000 0.7197 0.05555 0.04741 0.0116 0.1518 1.0000
7.250 0.7313 0.06208 0.05441 0.0106 0.1684 1.0000
7.500 0.6191 0.08985 0.08287 -0.0352 0.4310 1.0000
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Polar data table (+)
Polar graphs
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