WORTMANN FX M2 AIRFOIL (fxm2-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: WORTMANN FX M2 AIRFOIL (fxm2-il) Reynolds number: 50,000 Max Cl/Cd: 31.62 at α=2° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fxm2-il-50000.txt Download as CSV file: xf-fxm2-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: WORTMANN FX M2 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.500 -0.2840 0.10373 0.09725 -0.0145 1.0000 0.1251
-7.250 -0.2957 0.10368 0.09737 -0.0148 1.0000 0.1274
-7.000 -0.3061 0.10429 0.09812 -0.0192 1.0000 0.1285
-6.750 -0.2827 0.09653 0.09039 -0.0125 1.0000 0.1349
-6.500 -0.2813 0.09438 0.08835 -0.0124 1.0000 0.1405
-6.250 -0.2873 0.09407 0.08818 -0.0165 1.0000 0.1449
-6.000 -0.2821 0.09014 0.08437 -0.0151 1.0000 0.1484
-5.750 -0.2742 0.08691 0.08122 -0.0124 1.0000 0.1560
-5.500 -0.2737 0.08699 0.08134 -0.0216 1.0000 0.1634
-5.000 -0.2598 0.08125 0.07576 -0.0224 1.0000 0.1809
-4.750 -0.2574 0.07674 0.07143 -0.0138 1.0000 0.1878
-4.500 -0.2502 0.07438 0.06914 -0.0166 1.0000 0.2004
-4.250 -0.2428 0.07190 0.06674 -0.0172 1.0000 0.2158
-4.000 -0.2376 0.06927 0.06423 -0.0151 1.0000 0.2315
-3.750 -0.2284 0.06711 0.06212 -0.0167 1.0000 0.2548
-3.500 -0.2242 0.06471 0.05984 -0.0144 1.0000 0.2792
-3.250 -0.2219 0.06246 0.05773 -0.0111 1.0000 0.3049
-3.000 0.0785 0.04055 0.03546 -0.0047 1.0000 0.9722
-2.750 0.0256 0.04244 0.03763 0.0081 1.0000 0.9377
-2.500 -0.0226 0.04377 0.03923 0.0187 1.0000 0.9033
-2.250 -0.0627 0.04452 0.04023 0.0271 1.0000 0.8824
-2.000 -0.0992 0.04496 0.04091 0.0343 1.0000 0.8661
-1.750 -0.1267 0.04496 0.04113 0.0398 1.0000 0.8645
-1.500 -0.2330 0.05005 0.04646 0.0341 0.9768 0.6705
-1.000 0.2358 0.03471 0.02798 -0.0844 0.9179 0.2393
-0.750 0.3275 0.03138 0.02380 -0.0938 0.8934 0.1935
-0.500 0.3976 0.02879 0.02066 -0.0986 0.8612 0.1730
-0.250 0.4608 0.02647 0.01792 -0.1017 0.8254 0.1693
0.000 0.5123 0.02472 0.01572 -0.1023 0.7834 0.1678
0.250 0.5507 0.02372 0.01427 -0.1011 0.7365 0.1683
0.500 0.5818 0.02326 0.01342 -0.0993 0.6912 0.1758
0.750 0.6105 0.02310 0.01293 -0.0978 0.6506 0.1843
1.000 0.6383 0.02317 0.01276 -0.0965 0.6143 0.1949
1.250 0.6673 0.02330 0.01279 -0.0958 0.5846 0.2203
1.500 0.6849 0.02179 0.01310 -0.0929 0.5607 1.0000
1.750 0.7138 0.02260 0.01324 -0.0917 0.5394 1.0000
2.000 0.7416 0.02345 0.01355 -0.0908 0.5203 1.0000
2.250 0.7673 0.02433 0.01413 -0.0900 0.5016 1.0000
2.500 0.7936 0.02518 0.01468 -0.0894 0.4857 1.0000
2.750 0.8203 0.02608 0.01529 -0.0888 0.4720 1.0000
3.000 0.8456 0.02715 0.01626 -0.0884 0.4594 1.0000
3.250 0.8702 0.02836 0.01744 -0.0880 0.4481 1.0000
3.500 0.8952 0.02950 0.01851 -0.0875 0.4382 1.0000
3.750 0.9209 0.03053 0.01938 -0.0870 0.4285 1.0000
4.000 0.9434 0.03189 0.02080 -0.0865 0.4185 1.0000
4.250 0.9682 0.03310 0.02192 -0.0860 0.4103 1.0000
4.500 0.9905 0.03451 0.02338 -0.0854 0.4012 1.0000
4.750 1.0114 0.03612 0.02510 -0.0848 0.3928 1.0000
5.000 1.0351 0.03743 0.02637 -0.0842 0.3851 1.0000
5.250 1.0521 0.03950 0.02867 -0.0835 0.3771 1.0000
5.500 1.0783 0.04047 0.02947 -0.0829 0.3694 1.0000
5.750 1.0909 0.04301 0.03233 -0.0821 0.3611 1.0000
6.000 1.1121 0.04464 0.03400 -0.0814 0.3537 1.0000
6.250 1.1292 0.04656 0.03601 -0.0805 0.3448 1.0000
6.500 1.1393 0.04922 0.03888 -0.0795 0.3356 1.0000
6.750 1.1592 0.05060 0.04024 -0.0785 0.3262 1.0000
7.000 1.1763 0.05237 0.04208 -0.0775 0.3177 1.0000
7.250 1.1708 0.05709 0.04715 -0.0766 0.3115 1.0000
7.500 1.1890 0.05901 0.04914 -0.0758 0.3051 1.0000
7.750 1.1695 0.06556 0.05601 -0.0754 0.3015 1.0000
8.000 1.1081 0.07707 0.06779 -0.0771 0.3015 1.0000
8.250 1.0555 0.08830 0.07911 -0.0809 0.3039 1.0000
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Polar data table (+)
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