NACA M2 AIRFOIL (m2-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA M2 AIRFOIL (m2-il) Reynolds number: 100,000 Max Cl/Cd: 27.62 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-m2-il-100000-n5.txt Download as CSV file: xf-m2-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA M2 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
------ -------- --------- --------- -------- -------- --------
-10.000 -0.7461 0.08470 0.07979 -0.0045 1.0000 0.0284
-9.750 -0.7609 0.07698 0.07203 -0.0107 1.0000 0.0282
-9.500 -0.7788 0.07091 0.06586 -0.0137 1.0000 0.0281
-9.250 -0.7950 0.06523 0.06005 -0.0147 1.0000 0.0280
-9.000 -0.8074 0.05917 0.05370 -0.0151 1.0000 0.0281
-8.750 -0.8151 0.05327 0.04737 -0.0147 1.0000 0.0283
-8.500 -0.8169 0.04783 0.04134 -0.0137 1.0000 0.0288
-8.250 -0.8101 0.04417 0.03745 -0.0130 1.0000 0.0302
-8.000 -0.7950 0.04238 0.03552 -0.0124 1.0000 0.0321
-7.750 -0.7814 0.03931 0.03207 -0.0115 1.0000 0.0339
-7.500 -0.7671 0.03548 0.02767 -0.0103 1.0000 0.0355
-7.250 -0.7492 0.03239 0.02394 -0.0092 1.0000 0.0384
-7.000 -0.7295 0.02973 0.02088 -0.0084 1.0000 0.0408
-6.750 -0.7075 0.02801 0.01898 -0.0078 1.0000 0.0430
-6.500 -0.6844 0.02672 0.01746 -0.0072 1.0000 0.0466
-6.250 -0.6603 0.02510 0.01546 -0.0065 1.0000 0.0498
-6.000 -0.6362 0.02346 0.01363 -0.0058 1.0000 0.0519
-5.750 -0.6124 0.02262 0.01279 -0.0054 1.0000 0.0556
-5.500 -0.5879 0.02163 0.01168 -0.0048 1.0000 0.0593
-5.250 -0.5635 0.02052 0.01042 -0.0041 1.0000 0.0620
-5.000 -0.5400 0.01955 0.00942 -0.0033 1.0000 0.0650
-4.750 -0.5163 0.01882 0.00868 -0.0027 1.0000 0.0693
-4.500 -0.4927 0.01811 0.00787 -0.0018 1.0000 0.0754
-4.250 -0.4690 0.01756 0.00736 -0.0012 1.0000 0.0856
-4.000 -0.4455 0.01697 0.00675 -0.0005 1.0000 0.0999
-3.750 -0.4221 0.01638 0.00615 0.0003 1.0000 0.1155
-3.500 -0.3986 0.01588 0.00564 0.0010 1.0000 0.1305
-3.250 -0.3750 0.01542 0.00518 0.0016 1.0000 0.1463
-3.000 -0.3515 0.01493 0.00478 0.0023 1.0000 0.1670
-2.750 -0.3286 0.01429 0.00437 0.0029 1.0000 0.2085
-2.500 -0.3113 0.01266 0.00412 0.0042 1.0000 0.4852
-2.250 -0.2915 0.01200 0.00408 0.0062 1.0000 0.6300
-2.000 -0.2708 0.01169 0.00413 0.0084 1.0000 0.7247
-1.750 -0.2484 0.01158 0.00418 0.0102 1.0000 0.7906
-1.500 -0.2220 0.01160 0.00430 0.0114 1.0000 0.8466
-1.250 -0.1916 0.01169 0.00440 0.0116 1.0000 0.8944
-1.000 -0.1604 0.01177 0.00444 0.0111 1.0000 0.9313
-0.750 -0.1218 0.01183 0.00445 0.0090 1.0000 0.9591
-0.500 -0.0732 0.01188 0.00445 0.0046 1.0000 0.9809
-0.250 -0.0165 0.01188 0.00444 -0.0016 1.0000 0.9981
0.000 0.0000 0.01187 0.00441 0.0000 1.0000 1.0000
0.250 0.0165 0.01188 0.00444 0.0016 0.9981 1.0000
0.500 0.0732 0.01188 0.00445 -0.0046 0.9809 1.0000
0.750 0.1218 0.01183 0.00445 -0.0090 0.9591 1.0000
1.000 0.1603 0.01177 0.00444 -0.0111 0.9314 1.0000
1.250 0.1916 0.01169 0.00440 -0.0116 0.8944 1.0000
1.500 0.2220 0.01160 0.00430 -0.0114 0.8466 1.0000
1.750 0.2483 0.01158 0.00418 -0.0102 0.7906 1.0000
2.000 0.2708 0.01169 0.00413 -0.0084 0.7245 1.0000
2.250 0.2915 0.01200 0.00408 -0.0062 0.6300 1.0000
2.500 0.3112 0.01266 0.00411 -0.0042 0.4850 1.0000
2.750 0.3286 0.01429 0.00437 -0.0029 0.2086 1.0000
3.000 0.3515 0.01493 0.00478 -0.0023 0.1671 1.0000
3.250 0.3749 0.01542 0.00518 -0.0016 0.1464 1.0000
3.500 0.3986 0.01588 0.00564 -0.0010 0.1305 1.0000
3.750 0.4221 0.01638 0.00615 -0.0003 0.1155 1.0000
4.000 0.4455 0.01697 0.00675 0.0005 0.0999 1.0000
4.250 0.4689 0.01756 0.00736 0.0012 0.0856 1.0000
4.500 0.4927 0.01811 0.00787 0.0018 0.0754 1.0000
4.750 0.5163 0.01882 0.00868 0.0027 0.0693 1.0000
5.000 0.5400 0.01955 0.00941 0.0033 0.0650 1.0000
5.250 0.5635 0.02052 0.01039 0.0041 0.0620 1.0000
5.500 0.5879 0.02163 0.01168 0.0048 0.0593 1.0000
5.750 0.6124 0.02262 0.01279 0.0054 0.0556 1.0000
6.000 0.6362 0.02347 0.01363 0.0058 0.0519 1.0000
6.250 0.6603 0.02510 0.01546 0.0065 0.0498 1.0000
6.500 0.6844 0.02672 0.01747 0.0072 0.0466 1.0000
6.750 0.7075 0.02801 0.01898 0.0077 0.0430 1.0000
7.000 0.7296 0.02973 0.02088 0.0083 0.0408 1.0000
7.250 0.7493 0.03240 0.02395 0.0092 0.0384 1.0000
7.500 0.7672 0.03549 0.02768 0.0103 0.0355 1.0000
7.750 0.7815 0.03932 0.03208 0.0115 0.0339 1.0000
8.000 0.7951 0.04241 0.03556 0.0124 0.0321 1.0000
8.250 0.8102 0.04419 0.03747 0.0130 0.0302 1.0000
8.500 0.8170 0.04785 0.04136 0.0137 0.0288 1.0000
8.750 0.8152 0.05330 0.04741 0.0147 0.0283 1.0000
9.000 0.8075 0.05922 0.05375 0.0151 0.0281 1.0000
9.250 0.7953 0.06527 0.06010 0.0146 0.0280 1.0000
9.500 0.7790 0.07098 0.06594 0.0136 0.0280 1.0000
9.750 0.7613 0.07707 0.07212 0.0106 0.0282 1.0000
10.000 0.7466 0.08481 0.07990 0.0043 0.0284 1.0000
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Polar data table (+)
Polar graphs
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