NACA M2 (nacam2-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: NACA M2 (nacam2-il) Reynolds number: 100,000 Max Cl/Cd: 33.2 at α=3.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-nacam2-il-100000.txt Download as CSV file: xf-nacam2-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: NACA M2
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.7000 0.09110 0.08626 0.0049 1.0000 0.1430
-8.500 -0.7008 0.08701 0.08220 0.0032 1.0000 0.1488
-8.250 -0.7450 0.07976 0.07485 -0.0074 1.0000 0.1544
-8.000 -0.7127 0.07743 0.07263 -0.0020 1.0000 0.1610
-7.750 -0.7261 0.07192 0.06702 -0.0059 1.0000 0.1704
-7.500 -0.7276 0.06802 0.06301 -0.0071 1.0000 0.1838
-7.000 -0.7231 0.04566 0.03884 -0.0125 1.0000 0.0948
-6.750 -0.7093 0.03941 0.03167 -0.0108 1.0000 0.0818
-6.500 -0.6905 0.03542 0.02730 -0.0098 1.0000 0.0795
-6.250 -0.6698 0.03237 0.02374 -0.0086 1.0000 0.0799
-6.000 -0.6473 0.03005 0.02088 -0.0074 1.0000 0.0820
-5.750 -0.6231 0.02776 0.01815 -0.0064 1.0000 0.0827
-5.500 -0.5984 0.02552 0.01560 -0.0056 1.0000 0.0846
-5.250 -0.5738 0.02375 0.01385 -0.0051 1.0000 0.0896
-5.000 -0.5479 0.02226 0.01219 -0.0043 1.0000 0.0930
-4.750 -0.5219 0.02099 0.01074 -0.0035 1.0000 0.0964
-4.500 -0.4977 0.01957 0.00946 -0.0028 1.0000 0.1029
-4.250 -0.4731 0.01864 0.00847 -0.0019 1.0000 0.1111
-4.000 -0.4509 0.01742 0.00744 -0.0007 1.0000 0.1212
-3.750 -0.4292 0.01628 0.00643 0.0005 1.0000 0.1417
-3.500 -0.4173 0.01340 0.00535 0.0028 1.0000 0.4067
-3.250 -0.4047 0.01219 0.00537 0.0071 1.0000 0.6692
-3.000 -0.3845 0.01201 0.00547 0.0103 1.0000 0.7763
-2.750 -0.3609 0.01211 0.00562 0.0131 1.0000 0.8528
-2.500 -0.3094 0.01287 0.00628 0.0117 1.0000 0.9328
-2.250 -0.2129 0.01352 0.00652 -0.0004 1.0000 0.9731
-2.000 -0.1332 0.01340 0.00615 -0.0110 1.0000 0.9963
-1.750 -0.1043 0.01302 0.00567 -0.0124 1.0000 1.0000
-1.500 -0.0867 0.01268 0.00526 -0.0115 1.0000 1.0000
-1.250 -0.0696 0.01241 0.00494 -0.0104 1.0000 1.0000
-1.000 -0.0533 0.01219 0.00469 -0.0089 1.0000 1.0000
-0.750 -0.0382 0.01202 0.00450 -0.0071 1.0000 1.0000
-0.500 -0.0246 0.01190 0.00437 -0.0049 1.0000 1.0000
-0.250 -0.0122 0.01183 0.00430 -0.0025 1.0000 1.0000
0.000 0.0000 0.01181 0.00427 0.0000 1.0000 1.0000
0.250 0.0122 0.01183 0.00430 0.0025 1.0000 1.0000
0.500 0.0246 0.01190 0.00437 0.0049 1.0000 1.0000
0.750 0.0382 0.01202 0.00450 0.0071 1.0000 1.0000
1.000 0.0533 0.01219 0.00469 0.0089 1.0000 1.0000
1.250 0.0696 0.01241 0.00494 0.0104 1.0000 1.0000
1.500 0.0867 0.01268 0.00526 0.0115 1.0000 1.0000
1.750 0.1043 0.01302 0.00566 0.0124 1.0000 1.0000
2.000 0.1331 0.01340 0.00614 0.0110 0.9963 1.0000
2.250 0.2129 0.01352 0.00652 0.0004 0.9731 1.0000
2.500 0.3092 0.01287 0.00628 -0.0116 0.9330 1.0000
2.750 0.3608 0.01211 0.00562 -0.0130 0.8528 1.0000
3.000 0.3845 0.01201 0.00547 -0.0103 0.7763 1.0000
3.250 0.4047 0.01219 0.00537 -0.0071 0.6694 1.0000
3.500 0.4173 0.01340 0.00535 -0.0028 0.4066 1.0000
3.750 0.4291 0.01628 0.00643 -0.0005 0.1418 1.0000
4.000 0.4509 0.01742 0.00744 0.0008 0.1212 1.0000
4.250 0.4731 0.01864 0.00846 0.0019 0.1111 1.0000
4.500 0.4977 0.01957 0.00946 0.0028 0.1029 1.0000
4.750 0.5218 0.02099 0.01074 0.0035 0.0964 1.0000
5.000 0.5479 0.02226 0.01219 0.0043 0.0930 1.0000
5.250 0.5738 0.02375 0.01385 0.0051 0.0897 1.0000
5.500 0.5984 0.02552 0.01560 0.0056 0.0846 1.0000
5.750 0.6231 0.02776 0.01815 0.0064 0.0827 1.0000
6.000 0.6473 0.03006 0.02088 0.0074 0.0820 1.0000
6.250 0.6698 0.03237 0.02375 0.0086 0.0799 1.0000
6.500 0.6905 0.03543 0.02730 0.0098 0.0795 1.0000
6.750 0.7093 0.03941 0.03167 0.0108 0.0818 1.0000
7.000 0.7249 0.04596 0.03924 0.0127 0.1001 1.0000
7.250 0.6287 0.05539 0.05082 0.0069 0.2047 1.0000
8.000 0.7131 0.07744 0.07264 0.0019 0.1609 1.0000
8.250 0.7458 0.07979 0.07487 0.0074 0.1543 1.0000
8.500 0.7010 0.08705 0.08224 -0.0033 0.1487 1.0000
8.750 0.7012 0.09106 0.08623 -0.0048 0.1429 1.0000
|
Polar data table (+)
Polar graphs
<< Back to NACA M2 (nacam2-il)