GOE 380 AIRFOIL (goe380-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 380 AIRFOIL (goe380-il) Reynolds number: 50,000 Max Cl/Cd: 40.89 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe380-il-50000-n5.txt Download as CSV file: xf-goe380-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 380 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
------ -------- --------- --------- -------- -------- --------
-7.750 -0.2745 0.10690 0.10066 -0.0264 1.0000 0.0572
-7.500 -0.2804 0.10598 0.09987 -0.0258 1.0000 0.0577
-7.250 -0.2852 0.10506 0.09909 -0.0259 1.0000 0.0581
-7.000 -0.2873 0.10396 0.09809 -0.0266 1.0000 0.0583
-6.750 -0.2886 0.10295 0.09718 -0.0277 1.0000 0.0585
-6.500 -0.2877 0.10177 0.09606 -0.0289 1.0000 0.0587
-6.250 -0.2862 0.09608 0.09050 -0.0249 1.0000 0.0596
-6.000 -0.2854 0.09235 0.08684 -0.0220 1.0000 0.0610
-5.750 -0.2855 0.08985 0.08442 -0.0206 1.0000 0.0628
-5.500 -0.2850 0.08770 0.08233 -0.0200 1.0000 0.0644
-5.250 -0.2834 0.08566 0.08032 -0.0199 1.0000 0.0662
-5.000 -0.2796 0.08370 0.07840 -0.0206 1.0000 0.0686
-4.750 -0.2403 0.08222 0.07674 -0.0320 0.9931 0.0717
-4.500 -0.2146 0.07686 0.07139 -0.0357 0.9854 0.0731
-4.250 -0.1895 0.07209 0.06662 -0.0384 0.9776 0.0760
-4.000 -0.1557 0.06833 0.06275 -0.0440 0.9681 0.0800
-3.750 -0.1012 0.06623 0.06029 -0.0549 0.9569 0.0852
-3.500 -0.0751 0.06147 0.05553 -0.0575 0.9476 0.0866
-3.250 -0.0416 0.05733 0.05129 -0.0613 0.9398 0.0897
-3.000 -0.0065 0.05421 0.04800 -0.0653 0.9287 0.0934
-2.750 0.0428 0.05230 0.04562 -0.0715 0.9175 0.0984
-2.250 0.1206 0.04399 0.03682 -0.0774 0.8998 0.0563
-2.000 0.1559 0.04100 0.03356 -0.0796 0.8889 0.0520
-1.750 0.1993 0.03799 0.03005 -0.0824 0.8797 0.0475
-1.500 0.2442 0.03541 0.02685 -0.0847 0.8711 0.0454
-1.000 0.3121 0.03132 0.02219 -0.0868 0.8470 0.0530
-0.750 0.3497 0.02932 0.01964 -0.0875 0.8347 0.0554
-0.500 0.3877 0.02746 0.01724 -0.0881 0.8219 0.0599
-0.250 0.4222 0.02623 0.01563 -0.0884 0.8081 0.0736
0.000 0.4626 0.02478 0.01371 -0.0895 0.7949 0.0935
0.250 0.4980 0.02352 0.01216 -0.0902 0.7811 0.1366
0.500 0.5287 0.02269 0.01117 -0.0901 0.7666 0.1610
0.750 0.5579 0.02222 0.01050 -0.0898 0.7518 0.1779
1.000 0.5863 0.02184 0.01004 -0.0895 0.7368 0.2070
1.250 0.6137 0.02137 0.00973 -0.0891 0.7220 0.2637
1.750 0.6832 0.02022 0.00918 -0.0909 0.6917 1.0000
2.000 0.7094 0.02042 0.00910 -0.0902 0.6766 1.0000
2.250 0.7353 0.02063 0.00909 -0.0895 0.6617 1.0000
2.500 0.7609 0.02087 0.00914 -0.0887 0.6472 1.0000
2.750 0.7864 0.02114 0.00924 -0.0880 0.6328 1.0000
3.000 0.8116 0.02143 0.00940 -0.0873 0.6184 1.0000
3.250 0.8366 0.02175 0.00962 -0.0866 0.6044 1.0000
3.500 0.8616 0.02210 0.00988 -0.0859 0.5907 1.0000
3.750 0.8864 0.02247 0.01017 -0.0852 0.5771 1.0000
4.000 0.9112 0.02287 0.01056 -0.0846 0.5639 1.0000
4.250 0.9360 0.02329 0.01094 -0.0839 0.5511 1.0000
4.500 0.9609 0.02372 0.01134 -0.0833 0.5385 1.0000
4.750 0.9842 0.02422 0.01187 -0.0825 0.5253 1.0000
5.000 1.0069 0.02473 0.01247 -0.0816 0.5117 1.0000
5.250 1.0291 0.02522 0.01301 -0.0806 0.4974 1.0000
5.500 1.0508 0.02572 0.01356 -0.0795 0.4831 1.0000
5.750 1.0721 0.02622 0.01415 -0.0783 0.4690 1.0000
6.000 1.0931 0.02676 0.01486 -0.0772 0.4555 1.0000
6.250 1.1140 0.02732 0.01557 -0.0761 0.4426 1.0000
6.500 1.1350 0.02790 0.01630 -0.0750 0.4303 1.0000
6.750 1.1561 0.02847 0.01703 -0.0738 0.4183 1.0000
7.000 1.1773 0.02903 0.01779 -0.0727 0.4066 1.0000
7.250 1.1974 0.02968 0.01865 -0.0715 0.3944 1.0000
7.500 1.2165 0.03040 0.01961 -0.0702 0.3820 1.0000
7.750 1.2357 0.03117 0.02063 -0.0689 0.3701 1.0000
8.000 1.2554 0.03197 0.02169 -0.0676 0.3587 1.0000
8.250 1.2758 0.03273 0.02279 -0.0664 0.3477 1.0000
8.500 1.2827 0.03303 0.02317 -0.0631 0.3230 1.0000
8.750 1.2837 0.03355 0.02375 -0.0592 0.2949 1.0000
9.000 1.2820 0.03437 0.02463 -0.0553 0.2650 1.0000
9.250 1.2789 0.03547 0.02576 -0.0515 0.2333 1.0000
9.500 1.2752 0.03694 0.02720 -0.0479 0.1973 1.0000
9.750 1.2666 0.03917 0.02913 -0.0447 0.1561 1.0000
10.000 1.2568 0.04205 0.03175 -0.0421 0.0973 1.0000
10.250 1.2354 0.04643 0.03559 -0.0402 0.0515 1.0000
10.500 1.2223 0.05048 0.03956 -0.0391 0.0433 1.0000
10.750 1.2109 0.05467 0.04384 -0.0386 0.0391 1.0000
11.000 1.1991 0.05922 0.04853 -0.0388 0.0368 1.0000
11.250 1.1899 0.06369 0.05318 -0.0392 0.0349 1.0000
11.500 1.1804 0.06844 0.05814 -0.0401 0.0334 1.0000
11.750 1.1698 0.07351 0.06342 -0.0413 0.0320 1.0000
12.000 1.1589 0.07881 0.06890 -0.0427 0.0310 1.0000
12.250 1.1485 0.08409 0.07435 -0.0442 0.0303 1.0000
12.500 1.1366 0.08974 0.08014 -0.0459 0.0295 1.0000
12.750 1.1263 0.09520 0.08570 -0.0476 0.0288 1.0000
13.000 1.1209 0.09990 0.09058 -0.0490 0.0283 1.0000
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Polar data table (+)
Polar graphs
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