NACA M4 AIRFOIL (m4-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA M4 AIRFOIL (m4-il) Reynolds number: 50,000 Max Cl/Cd: 33.13 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-m4-il-50000.txt Download as CSV file: xf-m4-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: NACA M4 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.6108 0.11077 0.10446 0.0258 1.0000 0.1630
-8.000 -0.6021 0.10606 0.09978 0.0261 1.0000 0.1709
-7.750 -0.6097 0.10362 0.09742 0.0216 1.0000 0.1777
-7.500 -0.5984 0.09874 0.09256 0.0228 1.0000 0.1875
-7.250 -0.6001 0.09526 0.08913 0.0184 1.0000 0.1949
-7.000 -0.5981 0.09233 0.08619 0.0145 1.0000 0.2067
-6.750 -0.5880 0.08781 0.08169 0.0149 1.0000 0.2201
-6.500 -0.5825 0.08427 0.07814 0.0124 1.0000 0.2349
-6.250 -0.5712 0.07940 0.07334 0.0139 1.0000 0.2513
-6.000 -0.5601 0.07542 0.06934 0.0152 1.0000 0.2731
-5.750 -0.5530 0.07188 0.06583 0.0155 1.0000 0.3036
-5.500 -0.5450 0.06817 0.06220 0.0191 1.0000 0.3442
-5.250 -0.2397 0.05171 0.04499 0.0300 1.0000 1.0000
-5.000 -0.2266 0.04893 0.04222 0.0282 1.0000 1.0000
-4.750 -0.2133 0.04622 0.03950 0.0263 1.0000 1.0000
-4.250 -0.3410 0.04908 0.04289 0.0523 1.0000 0.8633
-4.000 -0.3903 0.04789 0.04195 0.0565 1.0000 0.7934
-3.750 -0.4316 0.04565 0.03997 0.0576 1.0000 0.7389
-3.500 -0.3285 0.03754 0.02908 -0.0096 1.0000 0.2324
-3.250 -0.2872 0.03436 0.02487 -0.0111 1.0000 0.1779
-3.000 -0.2560 0.03181 0.02173 -0.0111 1.0000 0.1643
-2.750 -0.2276 0.02976 0.01928 -0.0110 1.0000 0.1647
-2.500 -0.1995 0.02757 0.01690 -0.0109 1.0000 0.1625
-2.250 -0.1708 0.02576 0.01478 -0.0107 1.0000 0.1601
-2.000 -0.1426 0.02425 0.01303 -0.0104 1.0000 0.1598
-1.750 -0.1150 0.02300 0.01156 -0.0101 1.0000 0.1619
-1.500 -0.0868 0.02189 0.01037 -0.0100 1.0000 0.1688
-1.250 -0.0613 0.02106 0.00952 -0.0097 1.0000 0.1827
-1.000 -0.0386 0.02033 0.00874 -0.0089 1.0000 0.1954
-0.750 0.0487 0.01555 0.00659 -0.0182 1.0000 1.0000
-0.500 0.0597 0.01587 0.00640 -0.0156 1.0000 1.0000
-0.250 0.0685 0.01627 0.00653 -0.0132 1.0000 1.0000
0.000 0.0781 0.01671 0.00676 -0.0111 1.0000 1.0000
0.250 0.0892 0.01719 0.00705 -0.0095 1.0000 1.0000
0.500 0.1017 0.01772 0.00742 -0.0083 1.0000 1.0000
0.750 0.1152 0.01829 0.00786 -0.0074 1.0000 1.0000
1.000 0.1328 0.01891 0.00837 -0.0074 0.9987 1.0000
1.250 0.1946 0.01957 0.00895 -0.0156 0.9804 1.0000
1.500 0.2538 0.02018 0.00954 -0.0231 0.9612 1.0000
1.750 0.3173 0.02072 0.01013 -0.0310 0.9429 1.0000
2.000 0.3727 0.02124 0.01077 -0.0372 0.9235 1.0000
2.250 0.4200 0.02177 0.01142 -0.0414 0.9037 1.0000
2.500 0.4619 0.02231 0.01209 -0.0442 0.8845 1.0000
2.750 0.4921 0.02299 0.01294 -0.0448 0.8638 1.0000
3.000 0.5239 0.02360 0.01369 -0.0452 0.8448 1.0000
3.250 0.5484 0.02434 0.01458 -0.0445 0.8250 1.0000
3.500 0.5727 0.02505 0.01544 -0.0435 0.8054 1.0000
3.750 0.5977 0.02562 0.01619 -0.0420 0.7869 1.0000
4.000 0.6176 0.02640 0.01721 -0.0403 0.7648 1.0000
4.250 0.6401 0.02678 0.01778 -0.0376 0.7446 1.0000
4.500 0.6595 0.02738 0.01861 -0.0352 0.7204 1.0000
4.750 0.6772 0.02705 0.01844 -0.0299 0.6904 1.0000
5.000 0.6863 0.02487 0.01626 -0.0194 0.6369 1.0000
5.250 0.6999 0.02324 0.01463 -0.0119 0.5866 1.0000
5.500 0.7132 0.02153 0.01291 -0.0049 0.5028 1.0000
5.750 0.7164 0.02391 0.01305 0.0007 0.2050 1.0000
6.000 0.7339 0.02657 0.01511 0.0021 0.1572 1.0000
6.250 0.7571 0.02867 0.01719 0.0038 0.1375 1.0000
6.500 0.7814 0.03083 0.01931 0.0052 0.1223 1.0000
6.750 0.8071 0.03337 0.02196 0.0063 0.1133 1.0000
7.000 0.8334 0.03618 0.02515 0.0074 0.1092 1.0000
7.250 0.8575 0.03936 0.02842 0.0082 0.1042 1.0000
7.500 0.8781 0.04278 0.03244 0.0090 0.1007 1.0000
7.750 0.8974 0.04676 0.03698 0.0097 0.1007 1.0000
8.000 0.9148 0.05131 0.04193 0.0103 0.1021 1.0000
8.250 0.9229 0.05613 0.04769 0.0107 0.1066 1.0000
8.500 0.9235 0.06218 0.05436 0.0103 0.1121 1.0000
8.750 0.9397 0.06802 0.06018 0.0106 0.1164 1.0000
9.000 0.9024 0.07523 0.06824 0.0067 0.1245 1.0000
9.250 0.8910 0.08195 0.07511 0.0039 0.1323 1.0000
9.500 0.8789 0.08987 0.08310 0.0003 0.1442 1.0000
9.750 0.7648 0.08321 0.07664 0.0086 0.1305 1.0000
10.000 0.7022 0.09614 0.08943 -0.0025 0.1405 1.0000
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Polar data table (+)
Polar graphs
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