NACA M4 AIRFOIL (m4-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA M4 AIRFOIL (m4-il) Reynolds number: 500,000 Max Cl/Cd: 71.94 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-m4-il-500000.txt Download as CSV file: xf-m4-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.5236 0.13926 0.13722 0.0294 1.0000 0.0139
-11.250 -0.5224 0.13568 0.13364 0.0282 1.0000 0.0139
-9.750 -0.6480 0.12162 0.11953 0.0397 1.0000 0.0144
-9.500 -0.6423 0.11820 0.11610 0.0395 1.0000 0.0147
-9.250 -0.6378 0.11476 0.11268 0.0385 1.0000 0.0150
-9.000 -0.6339 0.11120 0.10913 0.0371 1.0000 0.0154
-8.750 -0.6304 0.10753 0.10545 0.0354 1.0000 0.0158
-8.500 -0.6274 0.10375 0.10169 0.0334 1.0000 0.0162
-8.250 -0.6245 0.09993 0.09788 0.0312 1.0000 0.0170
-7.250 -0.5973 0.08200 0.07991 0.0110 1.0000 0.0194
-7.000 -0.5848 0.07716 0.07502 0.0076 1.0000 0.0195
-6.750 -0.5711 0.07221 0.07000 0.0047 1.0000 0.0195
-6.500 -0.5562 0.06714 0.06484 0.0022 1.0000 0.0196
-6.000 -0.5309 0.05344 0.05084 -0.0021 1.0000 0.0199
-5.750 -0.5189 0.04928 0.04660 -0.0027 1.0000 0.0207
-5.500 -0.5003 0.04708 0.04434 -0.0031 1.0000 0.0216
-5.250 -0.4791 0.04430 0.04145 -0.0036 1.0000 0.0229
-3.250 -0.2813 0.01782 0.01249 -0.0010 0.9035 0.0350
-3.000 -0.2574 0.01640 0.01070 0.0004 0.8784 0.0363
-2.750 -0.2322 0.01543 0.00946 0.0014 0.8568 0.0376
-2.500 -0.2060 0.01434 0.00811 0.0021 0.8373 0.0379
-2.250 -0.1793 0.01364 0.00722 0.0027 0.8194 0.0386
-2.000 -0.1525 0.01280 0.00616 0.0031 0.8032 0.0401
-1.750 -0.1259 0.01175 0.00497 0.0036 0.7884 0.0407
-1.500 -0.0992 0.01105 0.00418 0.0040 0.7743 0.0414
-1.250 -0.0723 0.01055 0.00360 0.0043 0.7609 0.0419
-1.000 -0.0453 0.01015 0.00314 0.0045 0.7481 0.0428
-0.750 -0.0181 0.00984 0.00278 0.0047 0.7360 0.0444
-0.500 0.0093 0.00957 0.00246 0.0049 0.7244 0.0454
-0.250 0.0368 0.00936 0.00219 0.0051 0.7132 0.0470
0.000 0.0645 0.00920 0.00198 0.0052 0.7022 0.0496
0.250 0.0925 0.00908 0.00181 0.0053 0.6908 0.0523
0.500 0.1204 0.00892 0.00166 0.0053 0.6797 0.0618
0.750 0.1436 0.00751 0.00158 0.0055 0.6694 0.5117
1.000 0.2126 0.00644 0.00185 -0.0030 0.6569 1.0000
1.250 0.2393 0.00648 0.00180 -0.0028 0.6457 1.0000
1.500 0.2660 0.00650 0.00177 -0.0025 0.6338 1.0000
1.750 0.2927 0.00654 0.00176 -0.0022 0.6219 1.0000
2.000 0.3193 0.00659 0.00177 -0.0020 0.6099 1.0000
2.250 0.3459 0.00664 0.00178 -0.0017 0.5969 1.0000
2.500 0.3723 0.00671 0.00177 -0.0014 0.5772 1.0000
2.750 0.3987 0.00678 0.00178 -0.0011 0.5559 1.0000
3.000 0.4252 0.00686 0.00184 -0.0008 0.5394 1.0000
3.250 0.4516 0.00697 0.00189 -0.0005 0.5202 1.0000
3.500 0.4780 0.00711 0.00195 -0.0003 0.4920 1.0000
3.750 0.5044 0.00726 0.00203 0.0000 0.4648 1.0000
4.000 0.5306 0.00747 0.00216 0.0002 0.4319 1.0000
4.250 0.5568 0.00774 0.00230 0.0004 0.3900 1.0000
4.500 0.5827 0.00820 0.00249 0.0005 0.3192 1.0000
4.750 0.6067 0.00967 0.00309 0.0000 0.1312 1.0000
5.000 0.6317 0.01076 0.00376 0.0000 0.0476 1.0000
5.250 0.6575 0.01131 0.00434 0.0002 0.0376 1.0000
5.500 0.6832 0.01189 0.00496 0.0004 0.0314 1.0000
5.750 0.7083 0.01275 0.00591 0.0007 0.0273 1.0000
6.000 0.7340 0.01320 0.00641 0.0009 0.0241 1.0000
6.250 0.7589 0.01390 0.00715 0.0012 0.0214 1.0000
6.500 0.7804 0.01571 0.00908 0.0018 0.0194 1.0000
6.750 0.8052 0.01639 0.00985 0.0022 0.0185 1.0000
7.000 0.8293 0.01730 0.01084 0.0027 0.0173 1.0000
7.250 0.8537 0.01796 0.01156 0.0031 0.0158 1.0000
7.500 0.8773 0.01887 0.01252 0.0035 0.0148 1.0000
7.750 0.8992 0.02044 0.01420 0.0041 0.0140 1.0000
8.000 0.9175 0.02406 0.01808 0.0052 0.0134 1.0000
8.250 0.9377 0.02649 0.02083 0.0060 0.0130 1.0000
8.500 0.9565 0.02918 0.02385 0.0070 0.0129 1.0000
9.000 0.9858 0.03654 0.03182 0.0090 0.0136 1.0000
9.250 0.9964 0.04008 0.03569 0.0100 0.0136 1.0000
12.500 0.6807 0.12015 0.11795 -0.0104 0.0209 1.0000
12.750 0.6787 0.12338 0.12121 -0.0110 0.0204 1.0000
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Polar data table (+)
Polar graphs
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