NACA M5 AIRFOIL (m5-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA M5 AIRFOIL (m5-il) Reynolds number: 50,000 Max Cl/Cd: 32.67 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-m5-il-50000.txt Download as CSV file: xf-m5-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: NACA M5 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
------ -------- --------- --------- -------- -------- --------
-8.000 -0.6026 0.10289 0.09658 0.0177 1.0000 0.2328
-7.750 -0.5896 0.09831 0.09200 0.0190 1.0000 0.2464
-7.500 -0.5842 0.09435 0.08808 0.0192 1.0000 0.2602
-7.250 -0.5865 0.09094 0.08472 0.0179 1.0000 0.2764
-7.000 -0.5751 0.08674 0.08056 0.0199 1.0000 0.2975
-6.750 -0.5802 0.08386 0.07772 0.0187 1.0000 0.3214
-6.500 -0.5662 0.07990 0.07377 0.0218 1.0000 0.3488
-6.000 -0.5512 0.07344 0.06741 0.0283 1.0000 0.4242
-5.250 -0.1819 0.05213 0.04513 0.0188 1.0000 1.0000
-4.750 -0.2922 0.05468 0.04809 0.0418 1.0000 0.8737
-4.250 -0.4019 0.04119 0.03275 -0.0102 1.0000 0.2113
-4.000 -0.3709 0.03813 0.02875 -0.0111 1.0000 0.1884
-3.750 -0.3460 0.03520 0.02567 -0.0110 1.0000 0.1841
-3.500 -0.3176 0.03295 0.02265 -0.0107 1.0000 0.1737
-3.250 -0.2932 0.03072 0.02023 -0.0102 1.0000 0.1718
-3.000 -0.2698 0.02895 0.01818 -0.0094 1.0000 0.1713
-2.750 -0.2492 0.02756 0.01653 -0.0083 1.0000 0.1752
-2.500 -0.2305 0.02634 0.01530 -0.0071 1.0000 0.1810
-2.250 -0.2107 0.02533 0.01408 -0.0060 1.0000 0.1844
-2.000 -0.1897 0.02452 0.01301 -0.0049 1.0000 0.1887
-1.750 -0.1647 0.02357 0.01210 -0.0047 1.0000 0.1971
-1.500 -0.1409 0.02296 0.01145 -0.0045 1.0000 0.2137
-1.250 -0.0139 0.01762 0.00903 -0.0194 1.0000 1.0000
-1.000 -0.0093 0.01808 0.00900 -0.0161 1.0000 1.0000
-0.750 -0.0048 0.01855 0.00919 -0.0132 1.0000 1.0000
-0.500 0.0012 0.01903 0.00945 -0.0107 1.0000 1.0000
-0.250 0.0090 0.01954 0.00976 -0.0086 1.0000 1.0000
0.000 0.0187 0.02007 0.01012 -0.0070 1.0000 1.0000
0.250 0.0520 0.02067 0.01051 -0.0098 0.9929 1.0000
0.500 0.1091 0.02127 0.01092 -0.0169 0.9768 1.0000
0.750 0.1661 0.02185 0.01138 -0.0238 0.9606 1.0000
1.000 0.2241 0.02237 0.01183 -0.0306 0.9446 1.0000
1.250 0.2844 0.02280 0.01226 -0.0377 0.9287 1.0000
1.500 0.3338 0.02326 0.01274 -0.0425 0.9119 1.0000
1.750 0.3715 0.02379 0.01330 -0.0448 0.8940 1.0000
2.000 0.4077 0.02432 0.01388 -0.0467 0.8766 1.0000
2.250 0.4411 0.02487 0.01451 -0.0478 0.8595 1.0000
2.500 0.4716 0.02543 0.01514 -0.0483 0.8428 1.0000
2.750 0.4997 0.02601 0.01579 -0.0481 0.8264 1.0000
3.000 0.5258 0.02660 0.01649 -0.0474 0.8103 1.0000
3.250 0.5463 0.02740 0.01737 -0.0462 0.7929 1.0000
3.500 0.5673 0.02818 0.01826 -0.0450 0.7756 1.0000
3.750 0.5888 0.02894 0.01913 -0.0437 0.7587 1.0000
4.000 0.6105 0.02966 0.01998 -0.0423 0.7418 1.0000
4.250 0.6324 0.03031 0.02080 -0.0406 0.7250 1.0000
4.500 0.6547 0.03086 0.02149 -0.0387 0.7081 1.0000
4.750 0.6751 0.03152 0.02230 -0.0367 0.6896 1.0000
5.000 0.6943 0.03222 0.02318 -0.0347 0.6692 1.0000
5.250 0.7167 0.03238 0.02355 -0.0319 0.6500 1.0000
5.500 0.7372 0.03266 0.02402 -0.0292 0.6281 1.0000
5.750 0.7589 0.03146 0.02295 -0.0239 0.5993 1.0000
6.000 0.7795 0.02841 0.01981 -0.0158 0.5583 1.0000
6.250 0.7990 0.02668 0.01818 -0.0106 0.5160 1.0000
6.500 0.8162 0.02498 0.01653 -0.0054 0.4514 1.0000
6.750 0.8174 0.02573 0.01582 0.0008 0.2488 1.0000
7.000 0.8280 0.02871 0.01792 0.0031 0.1787 1.0000
7.250 0.8463 0.03100 0.01995 0.0048 0.1497 1.0000
7.500 0.8695 0.03325 0.02212 0.0063 0.1329 1.0000
7.750 0.8935 0.03561 0.02452 0.0074 0.1205 1.0000
8.000 0.9195 0.03858 0.02749 0.0083 0.1141 1.0000
8.250 0.9405 0.04141 0.03083 0.0095 0.1088 1.0000
8.500 0.9619 0.04447 0.03393 0.0102 0.1030 1.0000
8.750 0.9797 0.04849 0.03830 0.0112 0.1014 1.0000
9.000 0.9933 0.05258 0.04294 0.0123 0.1014 1.0000
9.250 1.0040 0.05706 0.04785 0.0133 0.1017 1.0000
9.500 1.0106 0.06169 0.05288 0.0142 0.1019 1.0000
9.750 0.9861 0.06646 0.05867 0.0155 0.1057 1.0000
10.000 0.9629 0.07225 0.06486 0.0155 0.1087 1.0000
10.250 0.9401 0.07775 0.07055 0.0150 0.1111 1.0000
10.500 0.9206 0.08321 0.07609 0.0140 0.1131 1.0000
10.750 0.9144 0.08888 0.08178 0.0129 0.1147 1.0000
11.000 0.8295 0.10619 0.09902 -0.0042 0.1253 1.0000
11.250 0.6713 0.10910 0.10210 0.0013 0.1399 1.0000
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Polar data table (+)
Polar graphs
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