NACA M3 AIRFOIL (m3-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA M3 AIRFOIL (m3-il) Reynolds number: 50,000 Max Cl/Cd: 27.33 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-m3-il-50000.txt Download as CSV file: xf-m3-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: NACA M3 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
------ -------- --------- --------- -------- -------- --------
-10.000 -0.7223 0.08756 0.08003 -0.0204 1.0000 0.1683
-9.750 -0.7340 0.08121 0.07365 -0.0224 1.0000 0.1633
-9.500 -0.8167 0.07118 0.06331 -0.0239 1.0000 0.1508
-9.250 -0.8235 0.06643 0.05839 -0.0229 1.0000 0.1496
-9.000 -0.8316 0.06182 0.05353 -0.0215 1.0000 0.1487
-8.750 -0.8370 0.05748 0.04886 -0.0197 1.0000 0.1482
-8.500 -0.8382 0.05342 0.04441 -0.0177 1.0000 0.1481
-8.250 -0.8346 0.04967 0.04024 -0.0156 1.0000 0.1483
-8.000 -0.8266 0.04621 0.03634 -0.0136 1.0000 0.1487
-7.750 -0.8160 0.04309 0.03274 -0.0115 1.0000 0.1501
-7.500 -0.8017 0.04031 0.02961 -0.0098 1.0000 0.1535
-7.250 -0.7812 0.03818 0.02744 -0.0087 1.0000 0.1594
-7.000 -0.7632 0.03591 0.02477 -0.0071 1.0000 0.1650
-6.750 -0.7409 0.03366 0.02242 -0.0060 1.0000 0.1714
-6.500 -0.7201 0.03188 0.02037 -0.0046 1.0000 0.1824
-6.250 -0.6973 0.03010 0.01862 -0.0035 1.0000 0.1980
-6.000 -0.6734 0.02828 0.01708 -0.0025 1.0000 0.2198
-5.750 -0.6539 0.02660 0.01563 -0.0007 1.0000 0.2573
-5.500 -0.6382 0.02490 0.01447 0.0018 1.0000 0.3157
-5.250 -0.6272 0.02349 0.01369 0.0053 1.0000 0.3967
-5.000 -0.6178 0.02260 0.01341 0.0096 1.0000 0.4863
-4.750 -0.6054 0.02227 0.01355 0.0143 1.0000 0.5676
-4.500 -0.5887 0.02238 0.01393 0.0188 1.0000 0.6345
-4.250 -0.5687 0.02280 0.01445 0.0232 1.0000 0.6905
-4.000 -0.5447 0.02351 0.01516 0.0273 1.0000 0.7398
-3.750 -0.5109 0.02454 0.01609 0.0300 1.0000 0.7842
-3.500 -0.4689 0.02549 0.01682 0.0306 1.0000 0.8260
-3.250 -0.3880 0.02679 0.01773 0.0244 1.0000 0.8632
-3.000 -0.2913 0.02731 0.01782 0.0133 1.0000 0.8979
-2.750 -0.2139 0.02701 0.01721 0.0041 1.0000 0.9292
-2.500 -0.1425 0.02628 0.01624 -0.0050 1.0000 0.9579
-2.250 -0.0683 0.02519 0.01498 -0.0153 1.0000 0.9841
-2.000 -0.0118 0.02404 0.01371 -0.0229 1.0000 1.0000
-1.750 -0.0031 0.02344 0.01310 -0.0217 1.0000 1.0000
-1.500 0.0039 0.02293 0.01260 -0.0199 1.0000 1.0000
-1.250 0.0087 0.02252 0.01221 -0.0177 1.0000 1.0000
-1.000 0.0112 0.02220 0.01191 -0.0150 1.0000 1.0000
-0.750 0.0115 0.02197 0.01169 -0.0118 1.0000 1.0000
-0.500 0.0094 0.02181 0.01154 -0.0082 1.0000 1.0000
-0.250 0.0052 0.02172 0.01146 -0.0042 1.0000 1.0000
0.000 0.0000 0.02169 0.01144 0.0000 1.0000 1.0000
0.250 -0.0052 0.02172 0.01146 0.0042 1.0000 1.0000
0.500 -0.0094 0.02181 0.01154 0.0082 1.0000 1.0000
0.750 -0.0115 0.02196 0.01169 0.0118 1.0000 1.0000
1.000 -0.0112 0.02220 0.01190 0.0150 1.0000 1.0000
1.250 -0.0087 0.02252 0.01220 0.0177 1.0000 1.0000
1.500 -0.0039 0.02293 0.01259 0.0199 1.0000 1.0000
1.750 0.0031 0.02343 0.01309 0.0217 1.0000 1.0000
2.000 0.0119 0.02404 0.01370 0.0229 1.0000 1.0000
2.250 0.0682 0.02518 0.01496 0.0153 0.9841 1.0000
2.500 0.1424 0.02627 0.01623 0.0050 0.9580 1.0000
2.750 0.2138 0.02700 0.01720 -0.0041 0.9292 1.0000
3.000 0.2912 0.02731 0.01781 -0.0133 0.8980 1.0000
3.250 0.3878 0.02678 0.01773 -0.0243 0.8632 1.0000
3.500 0.4690 0.02548 0.01681 -0.0307 0.8261 1.0000
3.750 0.5108 0.02454 0.01609 -0.0300 0.7843 1.0000
4.000 0.5446 0.02351 0.01516 -0.0273 0.7399 1.0000
4.250 0.5687 0.02280 0.01445 -0.0232 0.6906 1.0000
4.500 0.5886 0.02238 0.01393 -0.0188 0.6346 1.0000
4.750 0.6053 0.02227 0.01355 -0.0143 0.5677 1.0000
5.000 0.6177 0.02260 0.01341 -0.0096 0.4864 1.0000
5.250 0.6272 0.02348 0.01369 -0.0053 0.3968 1.0000
5.500 0.6381 0.02490 0.01447 -0.0018 0.3159 1.0000
5.750 0.6538 0.02659 0.01563 0.0007 0.2574 1.0000
6.000 0.6734 0.02827 0.01708 0.0025 0.2198 1.0000
6.250 0.6972 0.03010 0.01862 0.0035 0.1980 1.0000
6.500 0.7200 0.03187 0.02036 0.0046 0.1824 1.0000
6.750 0.7409 0.03366 0.02242 0.0060 0.1714 1.0000
7.000 0.7632 0.03591 0.02477 0.0071 0.1650 1.0000
7.250 0.7812 0.03817 0.02744 0.0087 0.1594 1.0000
7.500 0.8017 0.04031 0.02960 0.0098 0.1535 1.0000
7.750 0.8160 0.04309 0.03274 0.0115 0.1501 1.0000
8.000 0.8266 0.04621 0.03634 0.0136 0.1487 1.0000
8.250 0.8346 0.04967 0.04024 0.0156 0.1483 1.0000
8.500 0.8382 0.05342 0.04442 0.0176 0.1481 1.0000
8.750 0.8371 0.05748 0.04886 0.0196 0.1482 1.0000
9.000 0.8317 0.06183 0.05354 0.0214 0.1487 1.0000
9.250 0.8236 0.06644 0.05841 0.0229 0.1496 1.0000
9.500 0.8169 0.07120 0.06332 0.0238 0.1508 1.0000
9.750 0.7344 0.08125 0.07369 0.0223 0.1633 1.0000
10.000 0.7228 0.08761 0.08008 0.0203 0.1683 1.0000
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Polar data table (+)
Polar graphs
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