WORTMANN FX M2 AIRFOIL (fxm2-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: WORTMANN FX M2 AIRFOIL (fxm2-il) Reynolds number: 50,000 Max Cl/Cd: 35.69 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fxm2-il-50000-n5.txt Download as CSV file: xf-fxm2-il-50000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.2857 0.10769 0.10090 -0.0170 1.0000 0.0741
-7.750 -0.2929 0.10695 0.10032 -0.0179 1.0000 0.0750
-7.500 -0.3007 0.10608 0.09958 -0.0191 1.0000 0.0753
-7.250 -0.2809 0.10014 0.09368 -0.0162 1.0000 0.0777
-7.000 -0.2774 0.09757 0.09120 -0.0153 1.0000 0.0799
-6.750 -0.2772 0.09539 0.08914 -0.0150 1.0000 0.0824
-6.500 -0.2776 0.09350 0.08736 -0.0166 1.0000 0.0850
-6.250 -0.2774 0.09215 0.08611 -0.0216 1.0000 0.0865
-6.000 -0.2720 0.08864 0.08271 -0.0209 1.0000 0.0878
-5.750 -0.2656 0.08536 0.07953 -0.0180 1.0000 0.0907
-5.500 -0.2598 0.08283 0.07708 -0.0185 1.0000 0.0943
-5.000 -0.2442 0.07735 0.07173 -0.0235 1.0000 0.1015
-4.750 -0.2373 0.07467 0.06913 -0.0222 1.0000 0.1060
-4.250 -0.2151 0.06909 0.06365 -0.0257 1.0000 0.1182
-4.000 -0.1956 0.06647 0.06098 -0.0310 1.0000 0.1305
-3.750 -0.1911 0.06392 0.05858 -0.0278 1.0000 0.1374
-3.500 -0.1483 0.06036 0.05489 -0.0374 0.9920 0.1651
-3.250 -0.1126 0.05634 0.05094 -0.0408 0.9791 0.1861
-3.000 -0.0749 0.05294 0.04756 -0.0452 0.9644 0.2219
-2.500 0.0701 0.04301 0.03646 -0.0695 0.9340 0.1258
-2.250 0.1315 0.03861 0.03129 -0.0758 0.9169 0.0858
-2.000 0.1828 0.03550 0.02758 -0.0799 0.8972 0.0752
-1.750 0.2271 0.03265 0.02456 -0.0831 0.8757 0.0726
-1.500 0.2707 0.03059 0.02209 -0.0856 0.8489 0.0735
-1.250 0.3161 0.02874 0.01976 -0.0880 0.8212 0.0744
-1.000 0.3600 0.02697 0.01761 -0.0899 0.7878 0.0739
-0.750 0.4025 0.02559 0.01574 -0.0912 0.7474 0.0743
-0.500 0.4397 0.02448 0.01424 -0.0918 0.7045 0.0779
-0.250 0.4710 0.02378 0.01314 -0.0911 0.6623 0.0802
0.000 0.4984 0.02332 0.01226 -0.0898 0.6215 0.0815
0.250 0.5249 0.02305 0.01155 -0.0885 0.5856 0.0837
0.500 0.5500 0.02285 0.01102 -0.0872 0.5512 0.0883
0.750 0.5754 0.02269 0.01062 -0.0862 0.5218 0.0929
1.000 0.6011 0.02264 0.01033 -0.0854 0.4932 0.0966
1.250 0.6279 0.02267 0.01008 -0.0848 0.4707 0.1026
1.500 0.6551 0.02274 0.01003 -0.0845 0.4475 0.1146
1.750 0.6829 0.02280 0.00999 -0.0842 0.4288 0.1325
2.000 0.7004 0.02101 0.01009 -0.0818 0.4154 1.0000
2.250 0.7282 0.02157 0.01018 -0.0813 0.4010 1.0000
2.500 0.7558 0.02212 0.01044 -0.0810 0.3864 1.0000
2.750 0.7831 0.02265 0.01074 -0.0807 0.3730 1.0000
3.000 0.8100 0.02319 0.01104 -0.0804 0.3615 1.0000
3.250 0.8368 0.02377 0.01138 -0.0800 0.3516 1.0000
3.500 0.8638 0.02440 0.01178 -0.0798 0.3429 1.0000
3.750 0.8907 0.02509 0.01241 -0.0795 0.3338 1.0000
4.000 0.9174 0.02580 0.01302 -0.0793 0.3264 1.0000
4.250 0.9436 0.02651 0.01369 -0.0790 0.3185 1.0000
4.500 0.9693 0.02723 0.01442 -0.0786 0.3110 1.0000
4.750 0.9950 0.02788 0.01494 -0.0782 0.3043 1.0000
5.000 1.0200 0.02863 0.01570 -0.0777 0.2971 1.0000
5.250 1.0458 0.02932 0.01621 -0.0774 0.2915 1.0000
5.500 1.0699 0.03022 0.01720 -0.0769 0.2844 1.0000
5.750 1.0953 0.03100 0.01787 -0.0765 0.2786 1.0000
6.000 1.1177 0.03201 0.01907 -0.0759 0.2713 1.0000
6.250 1.1409 0.03291 0.02000 -0.0753 0.2648 1.0000
6.500 1.1630 0.03379 0.02098 -0.0746 0.2576 1.0000
6.750 1.1845 0.03476 0.02210 -0.0739 0.2510 1.0000
7.000 1.2078 0.03546 0.02276 -0.0733 0.2453 1.0000
7.250 1.2283 0.03647 0.02390 -0.0725 0.2387 1.0000
7.500 1.2524 0.03704 0.02432 -0.0720 0.2335 1.0000
7.750 1.2704 0.03831 0.02582 -0.0710 0.2266 1.0000
8.000 1.2943 0.03911 0.02654 -0.0705 0.2219 1.0000
8.250 1.3085 0.04093 0.02876 -0.0694 0.2160 1.0000
8.500 1.3285 0.04221 0.03013 -0.0686 0.2116 1.0000
8.750 1.3426 0.04407 0.03227 -0.0675 0.2069 1.0000
9.000 1.3550 0.04603 0.03457 -0.0663 0.2022 1.0000
9.250 1.3741 0.04731 0.03589 -0.0655 0.1987 1.0000
9.500 1.3783 0.05005 0.03904 -0.0640 0.1945 1.0000
9.750 1.3837 0.05257 0.04185 -0.0625 0.1907 1.0000
10.000 1.3962 0.05434 0.04374 -0.0614 0.1877 1.0000
10.250 1.4155 0.05556 0.04496 -0.0607 0.1853 1.0000
10.500 1.3894 0.06078 0.05070 -0.0582 0.1824 1.0000
10.750 1.3507 0.06655 0.05682 -0.0556 0.1802 1.0000
11.000 1.1992 0.08942 0.08006 -0.0647 0.1771 1.0000
11.250 1.1611 0.10150 0.09221 -0.0713 0.1735 1.0000
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Polar data table (+)
Polar graphs
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