WORTMANN FX 74-080 (fx74080-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: WORTMANN FX 74-080 (fx74080-il) Reynolds number: 50,000 Max Cl/Cd: 27.06 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx74080-il-50000-n5.txt Download as CSV file: xf-fx74080-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: WORTMANN FX 74-080
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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3980 0.11981 0.11368 -0.0360 1.0000 0.0699
-8.250 -0.4116 0.11920 0.11317 -0.0342 1.0000 0.0700
-8.000 -0.4281 0.11871 0.11279 -0.0323 1.0000 0.0702
-7.750 -0.4037 0.11072 0.10477 -0.0296 1.0000 0.0739
-7.500 -0.4111 0.10898 0.10310 -0.0276 1.0000 0.0753
-7.250 -0.4192 0.10728 0.10146 -0.0260 0.9997 0.0766
-7.000 -0.4155 0.10441 0.09863 -0.0290 0.9949 0.0800
-6.750 -0.4091 0.10184 0.09608 -0.0387 0.9869 0.0831
-6.500 -0.3982 0.09778 0.09203 -0.0435 0.9815 0.0843
-6.250 -0.3866 0.09314 0.08740 -0.0404 0.9795 0.0884
-6.000 -0.3754 0.08965 0.08389 -0.0447 0.9740 0.0940
-5.750 -0.3609 0.08575 0.07995 -0.0523 0.9681 0.0983
-5.500 -0.3459 0.08174 0.07592 -0.0524 0.9651 0.1036
-5.000 -0.3170 0.07434 0.06841 -0.0590 0.9550 0.1172
-4.750 -0.2959 0.07039 0.06435 -0.0637 0.9509 0.1280
-4.250 -0.2268 0.05969 0.05290 -0.0752 0.9420 0.0545
-4.000 -0.1859 0.05492 0.04753 -0.0805 0.9390 0.0430
-3.750 -0.1692 0.05159 0.04411 -0.0810 0.9346 0.0409
-3.500 -0.1409 0.04803 0.04021 -0.0833 0.9308 0.0389
-3.250 -0.1071 0.04469 0.03626 -0.0861 0.9278 0.0381
-3.000 -0.0708 0.04185 0.03279 -0.0887 0.9252 0.0412
-2.750 -0.0436 0.04001 0.03026 -0.0888 0.9206 0.0433
-2.500 -0.0132 0.03743 0.02725 -0.0900 0.9174 0.0445
-2.250 0.0205 0.03530 0.02459 -0.0911 0.9148 0.0445
-2.000 0.0554 0.03338 0.02225 -0.0924 0.9125 0.0457
-1.750 0.0784 0.03221 0.02077 -0.0914 0.9081 0.0472
-1.500 0.1058 0.03114 0.01940 -0.0910 0.9045 0.0507
-1.250 0.1380 0.03029 0.01815 -0.0914 0.9016 0.0573
-1.000 0.1704 0.02956 0.01731 -0.0926 0.8989 0.0789
-0.750 0.1931 0.02891 0.01642 -0.0918 0.8939 0.1025
-0.500 0.2193 0.02576 0.01599 -0.0912 0.8912 1.0000
-0.250 0.2510 0.02613 0.01574 -0.0921 0.8875 1.0000
0.000 0.2740 0.02655 0.01578 -0.0917 0.8823 1.0000
0.250 0.2992 0.02697 0.01589 -0.0917 0.8773 1.0000
0.500 0.3309 0.02738 0.01601 -0.0929 0.8737 1.0000
0.750 0.3502 0.02787 0.01631 -0.0920 0.8676 1.0000
1.000 0.3770 0.02833 0.01655 -0.0924 0.8630 1.0000
1.250 0.4097 0.02878 0.01683 -0.0937 0.8597 1.0000
1.500 0.4247 0.02936 0.01732 -0.0922 0.8526 1.0000
1.750 0.4537 0.02985 0.01772 -0.0929 0.8484 1.0000
2.000 0.4751 0.03042 0.01825 -0.0924 0.8427 1.0000
2.250 0.4991 0.03098 0.01882 -0.0924 0.8372 1.0000
2.500 0.5311 0.03146 0.01929 -0.0936 0.8335 1.0000
2.750 0.5450 0.03217 0.02001 -0.0919 0.8258 1.0000
3.000 0.5746 0.03269 0.02059 -0.0928 0.8215 1.0000
3.250 0.5913 0.03341 0.02137 -0.0916 0.8143 1.0000
3.500 0.6187 0.03398 0.02205 -0.0921 0.8092 1.0000
3.750 0.6378 0.03469 0.02287 -0.0913 0.8023 1.0000
4.000 0.6635 0.03529 0.02376 -0.0914 0.7964 1.0000
4.250 0.6830 0.03602 0.02464 -0.0907 0.7891 1.0000
4.500 0.7098 0.03658 0.02542 -0.0909 0.7828 1.0000
4.750 0.7272 0.03735 0.02640 -0.0899 0.7744 1.0000
5.000 0.7577 0.03783 0.02719 -0.0905 0.7686 1.0000
5.250 0.7732 0.03863 0.02826 -0.0891 0.7587 1.0000
5.500 0.7961 0.03925 0.02923 -0.0887 0.7503 1.0000
5.750 0.8288 0.03925 0.02999 -0.0888 0.7400 1.0000
6.250 0.8598 0.03177 0.01883 -0.0667 0.0658 1.0000
6.500 0.8662 0.03374 0.02081 -0.0641 0.0548 1.0000
6.750 0.8754 0.03547 0.02272 -0.0618 0.0465 1.0000
7.000 0.8849 0.03727 0.02468 -0.0597 0.0383 1.0000
7.250 0.8974 0.03900 0.02658 -0.0577 0.0342 1.0000
7.500 0.9334 0.04093 0.02864 -0.0568 0.0312 1.0000
7.750 1.0486 0.04512 0.03347 -0.0651 0.0289 1.0000
8.000 1.0900 0.04906 0.03791 -0.0662 0.0286 1.0000
8.250 1.1119 0.05241 0.04204 -0.0649 0.0271 1.0000
8.500 1.1254 0.05557 0.04567 -0.0629 0.0254 1.0000
8.750 1.1346 0.05878 0.04930 -0.0606 0.0245 1.0000
9.000 1.1384 0.06197 0.05283 -0.0580 0.0231 1.0000
9.250 1.1392 0.06537 0.05662 -0.0551 0.0230 1.0000
9.500 1.1359 0.06863 0.06024 -0.0519 0.0231 1.0000
9.750 1.1274 0.07197 0.06391 -0.0483 0.0234 1.0000
10.000 1.1164 0.07528 0.06752 -0.0451 0.0238 1.0000
10.250 1.1032 0.07874 0.07124 -0.0423 0.0241 1.0000
10.500 1.0880 0.08244 0.07518 -0.0401 0.0244 1.0000
10.750 1.0712 0.08643 0.07939 -0.0386 0.0246 1.0000
11.000 1.0538 0.09067 0.08382 -0.0379 0.0249 1.0000
11.250 1.0356 0.09536 0.08869 -0.0381 0.0252 1.0000
11.500 1.0169 0.10052 0.09399 -0.0391 0.0253 1.0000
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Polar data table (+)
Polar graphs
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