NACA M4 AIRFOIL (m4-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA M4 AIRFOIL (m4-il) Reynolds number: 100,000 Max Cl/Cd: 44.8 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-m4-il-100000-n5.txt Download as CSV file: xf-m4-il-100000-n5.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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.5910 0.10353 0.09901 0.0238 1.0000 0.0353
-8.000 -0.5886 0.09952 0.09503 0.0212 1.0000 0.0356
-7.750 -0.5868 0.09541 0.09096 0.0182 1.0000 0.0355
-7.500 -0.4818 0.07793 0.07375 0.0053 1.0000 0.0348
-7.000 -0.5655 0.07972 0.07517 0.0036 1.0000 0.0274
-6.750 -0.5559 0.07503 0.07043 0.0015 1.0000 0.0268
-6.500 -0.5435 0.07017 0.06550 -0.0011 1.0000 0.0266
-6.250 -0.5264 0.06496 0.06012 -0.0044 1.0000 0.0273
-5.750 -0.4960 0.05702 0.05199 -0.0071 1.0000 0.0318
-5.500 -0.4754 0.05125 0.04591 -0.0090 1.0000 0.0307
-5.250 -0.4546 0.04654 0.04088 -0.0099 1.0000 0.0308
-5.000 -0.4335 0.04324 0.03736 -0.0103 1.0000 0.0326
-4.750 -0.4101 0.03972 0.03351 -0.0106 1.0000 0.0360
-4.500 -0.3857 0.03536 0.02865 -0.0105 1.0000 0.0372
-4.250 -0.3596 0.03155 0.02418 -0.0101 1.0000 0.0395
-4.000 -0.3358 0.02880 0.02112 -0.0101 1.0000 0.0433
-3.750 -0.3098 0.02651 0.01848 -0.0100 1.0000 0.0451
-3.500 -0.2831 0.02479 0.01639 -0.0098 1.0000 0.0491
-3.250 -0.2553 0.02301 0.01417 -0.0096 1.0000 0.0517
-3.000 -0.2275 0.02138 0.01218 -0.0094 1.0000 0.0526
-2.750 -0.1999 0.02012 0.01064 -0.0094 1.0000 0.0536
-2.500 -0.1695 0.01875 0.00912 -0.0101 0.9843 0.0550
-2.250 -0.1331 0.01780 0.00812 -0.0122 0.9550 0.0596
-2.000 -0.0990 0.01710 0.00730 -0.0133 0.9301 0.0630
-1.750 -0.0690 0.01640 0.00649 -0.0135 0.9072 0.0635
-1.500 -0.0424 0.01586 0.00585 -0.0129 0.8857 0.0642
-1.250 -0.0174 0.01545 0.00532 -0.0120 0.8663 0.0652
-1.000 0.0074 0.01512 0.00487 -0.0110 0.8481 0.0666
-0.750 0.0324 0.01485 0.00448 -0.0100 0.8313 0.0688
-0.500 0.0577 0.01458 0.00415 -0.0092 0.8157 0.0737
-0.250 0.0837 0.01436 0.00389 -0.0085 0.8009 0.0851
0.000 0.1095 0.01381 0.00372 -0.0081 0.7867 0.2015
0.500 0.2015 0.01185 0.00368 -0.0149 0.7594 1.0000
0.750 0.2264 0.01195 0.00364 -0.0142 0.7457 1.0000
1.000 0.2514 0.01205 0.00363 -0.0135 0.7322 1.0000
1.250 0.2765 0.01215 0.00364 -0.0128 0.7190 1.0000
1.500 0.3017 0.01227 0.00368 -0.0122 0.7060 1.0000
1.750 0.3269 0.01239 0.00376 -0.0115 0.6933 1.0000
2.000 0.3522 0.01252 0.00384 -0.0109 0.6806 1.0000
2.250 0.3776 0.01266 0.00395 -0.0103 0.6680 1.0000
2.500 0.4031 0.01281 0.00410 -0.0097 0.6554 1.0000
2.750 0.4287 0.01296 0.00426 -0.0092 0.6424 1.0000
3.000 0.4545 0.01312 0.00445 -0.0087 0.6290 1.0000
3.250 0.4803 0.01328 0.00468 -0.0083 0.6155 1.0000
3.500 0.5061 0.01346 0.00491 -0.0078 0.6016 1.0000
3.750 0.5319 0.01363 0.00515 -0.0073 0.5865 1.0000
4.000 0.5574 0.01379 0.00537 -0.0067 0.5683 1.0000
4.250 0.5827 0.01393 0.00558 -0.0060 0.5432 1.0000
4.500 0.6075 0.01406 0.00571 -0.0052 0.5062 1.0000
4.750 0.6317 0.01428 0.00582 -0.0043 0.4546 1.0000
5.000 0.6562 0.01465 0.00608 -0.0037 0.4001 1.0000
5.250 0.6805 0.01519 0.00652 -0.0032 0.3290 1.0000
5.500 0.6995 0.01723 0.00744 -0.0031 0.1297 1.0000
5.750 0.7208 0.01897 0.00875 -0.0029 0.0668 1.0000
6.000 0.7430 0.02035 0.01014 -0.0024 0.0508 1.0000
6.250 0.7651 0.02157 0.01148 -0.0019 0.0406 1.0000
6.500 0.7860 0.02303 0.01315 -0.0010 0.0356 1.0000
6.750 0.8063 0.02448 0.01462 -0.0003 0.0304 1.0000
7.000 0.8267 0.02625 0.01650 0.0008 0.0280 1.0000
7.250 0.8485 0.02809 0.01855 0.0019 0.0260 1.0000
7.500 0.8704 0.02989 0.02058 0.0028 0.0231 1.0000
7.750 0.8912 0.03186 0.02278 0.0035 0.0211 1.0000
8.000 0.9109 0.03436 0.02554 0.0044 0.0200 1.0000
8.250 0.9285 0.03737 0.02893 0.0053 0.0193 1.0000
8.500 0.9425 0.04111 0.03306 0.0062 0.0187 1.0000
8.750 0.9504 0.04579 0.03819 0.0071 0.0181 1.0000
9.000 0.9597 0.04860 0.04151 0.0082 0.0175 1.0000
9.250 0.9639 0.05212 0.04551 0.0092 0.0169 1.0000
9.500 0.9623 0.05610 0.04989 0.0100 0.0166 1.0000
9.750 0.9552 0.06025 0.05437 0.0106 0.0165 1.0000
10.000 0.9419 0.06425 0.05861 0.0110 0.0166 1.0000
10.250 0.9256 0.06865 0.06319 0.0099 0.0166 1.0000
10.500 0.9090 0.07395 0.06866 0.0069 0.0167 1.0000
10.750 0.8922 0.08019 0.07503 0.0026 0.0168 1.0000
11.000 0.8757 0.08740 0.08234 -0.0027 0.0170 1.0000
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Polar data table (+)
Polar graphs
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