NACA M2 (nacam2-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA M2 (nacam2-il) Reynolds number: 200,000 Max Cl/Cd: 38.58 at α=2.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-nacam2-il-200000.txt Download as CSV file: xf-nacam2-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.7264 0.09674 0.09323 -0.0046 1.0000 0.0574
-9.750 -0.7451 0.09006 0.08648 -0.0113 1.0000 0.0574
-9.500 -0.7648 0.08554 0.08186 -0.0132 1.0000 0.0575
-9.000 -0.7533 0.07568 0.07215 -0.0119 1.0000 0.0603
-8.750 -0.7514 0.07237 0.06881 -0.0120 1.0000 0.0618
-8.500 -0.7538 0.06808 0.06442 -0.0131 1.0000 0.0637
-8.250 -0.7582 0.06310 0.05923 -0.0144 1.0000 0.0668
-7.750 -0.7585 0.05333 0.04895 -0.0147 1.0000 0.0736
-7.500 -0.7446 0.05069 0.04624 -0.0141 1.0000 0.0774
-7.250 -0.7398 0.04663 0.04173 -0.0134 1.0000 0.0862
-7.000 -0.7309 0.03400 0.02725 -0.0087 1.0000 0.0459
-6.750 -0.7125 0.02973 0.02261 -0.0076 1.0000 0.0453
-6.500 -0.6929 0.02648 0.01889 -0.0065 1.0000 0.0466
-6.250 -0.6709 0.02391 0.01618 -0.0059 1.0000 0.0488
-6.000 -0.6467 0.02220 0.01426 -0.0051 1.0000 0.0503
-5.750 -0.6220 0.02080 0.01270 -0.0044 1.0000 0.0522
-5.500 -0.5969 0.01979 0.01153 -0.0037 1.0000 0.0553
-5.250 -0.5716 0.01877 0.01035 -0.0030 1.0000 0.0570
-5.000 -0.5474 0.01732 0.00883 -0.0022 1.0000 0.0588
-4.750 -0.5239 0.01625 0.00781 -0.0015 1.0000 0.0626
-4.500 -0.4999 0.01548 0.00704 -0.0007 1.0000 0.0658
-4.250 -0.4761 0.01479 0.00630 0.0002 1.0000 0.0687
-4.000 -0.4532 0.01398 0.00551 0.0011 1.0000 0.0725
-3.750 -0.4299 0.01338 0.00492 0.0020 1.0000 0.0799
-3.500 -0.4068 0.01272 0.00433 0.0029 1.0000 0.0916
-3.250 -0.3869 0.01126 0.00361 0.0039 1.0000 0.2173
-3.000 -0.3696 0.00979 0.00328 0.0053 1.0000 0.4634
-2.750 -0.3500 0.00907 0.00317 0.0070 1.0000 0.6078
-2.500 -0.3296 0.00864 0.00319 0.0090 1.0000 0.7142
-2.250 -0.3090 0.00844 0.00327 0.0112 1.0000 0.7962
-2.000 -0.2876 0.00841 0.00339 0.0135 1.0000 0.8560
-1.750 -0.2629 0.00849 0.00350 0.0150 1.0000 0.9021
-1.500 -0.2234 0.00875 0.00376 0.0137 1.0000 0.9493
-1.250 -0.1571 0.00908 0.00398 0.0064 1.0000 0.9759
-1.000 -0.0975 0.00916 0.00397 -0.0001 1.0000 0.9874
-0.750 -0.0455 0.00914 0.00389 -0.0054 1.0000 0.9962
-0.500 -0.0142 0.00903 0.00376 -0.0068 1.0000 1.0000
-0.250 -0.0059 0.00893 0.00366 -0.0036 1.0000 1.0000
0.000 0.0000 0.00889 0.00363 0.0000 1.0000 1.0000
0.250 0.0059 0.00893 0.00366 0.0036 1.0000 1.0000
0.500 0.0142 0.00903 0.00376 0.0068 1.0000 1.0000
0.750 0.0455 0.00914 0.00389 0.0054 0.9962 1.0000
1.000 0.0975 0.00916 0.00397 0.0001 0.9874 1.0000
1.250 0.1571 0.00908 0.00398 -0.0065 0.9759 1.0000
1.500 0.2232 0.00876 0.00376 -0.0136 0.9497 1.0000
1.750 0.2629 0.00849 0.00350 -0.0150 0.9019 1.0000
2.000 0.2875 0.00841 0.00339 -0.0134 0.8559 1.0000
2.250 0.3089 0.00844 0.00327 -0.0112 0.7962 1.0000
2.500 0.3296 0.00864 0.00319 -0.0090 0.7143 1.0000
2.750 0.3499 0.00907 0.00317 -0.0070 0.6075 1.0000
3.000 0.3696 0.00979 0.00328 -0.0052 0.4634 1.0000
3.250 0.3869 0.01126 0.00361 -0.0039 0.2180 1.0000
3.500 0.4068 0.01272 0.00433 -0.0029 0.0916 1.0000
3.750 0.4299 0.01338 0.00492 -0.0020 0.0799 1.0000
4.000 0.4532 0.01398 0.00551 -0.0011 0.0725 1.0000
4.250 0.4760 0.01479 0.00630 -0.0002 0.0687 1.0000
4.500 0.4999 0.01548 0.00704 0.0007 0.0658 1.0000
4.750 0.5239 0.01625 0.00781 0.0015 0.0626 1.0000
5.000 0.5473 0.01732 0.00883 0.0022 0.0588 1.0000
5.250 0.5716 0.01877 0.01035 0.0030 0.0570 1.0000
5.500 0.5969 0.01979 0.01153 0.0037 0.0553 1.0000
5.750 0.6220 0.02081 0.01271 0.0044 0.0523 1.0000
6.000 0.6467 0.02221 0.01426 0.0051 0.0503 1.0000
6.250 0.6709 0.02391 0.01618 0.0059 0.0488 1.0000
6.500 0.6929 0.02652 0.01893 0.0064 0.0466 1.0000
6.750 0.7126 0.02972 0.02260 0.0076 0.0453 1.0000
7.000 0.7309 0.03402 0.02727 0.0087 0.0459 1.0000
9.750 0.5810 0.09080 0.08741 0.0021 0.0667 1.0000
10.000 0.5718 0.09630 0.09288 -0.0004 0.0646 1.0000
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Polar data table (+)
Polar graphs
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