GOE 275 (DAIMLER VI) AIRFOIL (goe275-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: GOE 275 (DAIMLER VI) AIRFOIL (goe275-il) Reynolds number: 100,000 Max Cl/Cd: 55.86 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe275-il-100000-n5.txt Download as CSV file: xf-goe275-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 275 (DAIMLER VI) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.500 -0.3162 0.09409 0.08943 -0.0229 1.0000 0.0355
-7.250 -0.3231 0.09239 0.08782 -0.0211 1.0000 0.0362
-7.000 -0.3284 0.09049 0.08600 -0.0200 1.0000 0.0368
-6.750 -0.3323 0.08846 0.08404 -0.0196 1.0000 0.0380
-6.500 -0.3352 0.08646 0.08210 -0.0208 1.0000 0.0395
-6.250 -0.3324 0.08441 0.08006 -0.0255 1.0000 0.0405
-6.000 -0.3084 0.08093 0.07644 -0.0351 0.9973 0.0409
-5.750 -0.2975 0.07580 0.07141 -0.0337 0.9940 0.0417
-5.500 -0.2788 0.07199 0.06760 -0.0349 0.9894 0.0431
-5.250 -0.2510 0.06805 0.06361 -0.0398 0.9841 0.0454
-5.000 -0.1887 0.06337 0.05844 -0.0567 0.9763 0.0513
-4.750 -0.1781 0.05896 0.05422 -0.0554 0.9703 0.0530
-4.500 -0.1467 0.05540 0.05060 -0.0592 0.9646 0.0566
-4.250 -0.0962 0.05149 0.04616 -0.0685 0.9554 0.0637
-4.000 -0.0728 0.04764 0.04244 -0.0699 0.9484 0.0664
-3.750 -0.0310 0.04440 0.03886 -0.0753 0.9402 0.0780
-3.500 0.0070 0.04236 0.03644 -0.0789 0.9310 0.0909
-3.250 0.0372 0.03850 0.03274 -0.0812 0.9243 0.0959
-2.750 0.1089 0.03380 0.02771 -0.0869 0.9078 0.1395
-2.250 0.1916 0.02882 0.02175 -0.0909 0.8922 0.1030
-2.000 0.2287 0.02579 0.01810 -0.0906 0.8822 0.0597
-1.750 0.2654 0.02419 0.01618 -0.0919 0.8737 0.0596
-1.500 0.2976 0.02276 0.01449 -0.0923 0.8624 0.0577
-1.250 0.3291 0.02155 0.01298 -0.0924 0.8496 0.0551
-1.000 0.3613 0.02058 0.01170 -0.0924 0.8358 0.0533
-0.750 0.3928 0.01983 0.01070 -0.0924 0.8202 0.0523
-0.500 0.4236 0.01895 0.00970 -0.0925 0.8025 0.0527
-0.250 0.4547 0.01813 0.00883 -0.0927 0.7830 0.0547
0.000 0.4840 0.01751 0.00812 -0.0924 0.7599 0.0552
0.250 0.5150 0.01694 0.00743 -0.0924 0.7352 0.0550
0.500 0.5445 0.01647 0.00686 -0.0922 0.7068 0.0550
0.750 0.5734 0.01612 0.00636 -0.0919 0.6757 0.0554
1.000 0.6012 0.01592 0.00597 -0.0914 0.6434 0.0559
1.250 0.6271 0.01587 0.00570 -0.0906 0.6123 0.0568
1.500 0.6526 0.01592 0.00554 -0.0898 0.5832 0.0598
1.750 0.6781 0.01603 0.00543 -0.0891 0.5563 0.0625
2.250 0.7284 0.01628 0.00532 -0.0876 0.5075 0.0671
2.500 0.7533 0.01648 0.00535 -0.0868 0.4863 0.0712
2.750 0.7782 0.01668 0.00544 -0.0861 0.4677 0.0803
3.000 0.8085 0.01521 0.00571 -0.0868 0.4516 1.0000
3.500 0.8574 0.01588 0.00605 -0.0853 0.4243 1.0000
3.750 0.8818 0.01622 0.00627 -0.0846 0.4124 1.0000
4.000 0.9064 0.01658 0.00653 -0.0839 0.4027 1.0000
4.250 0.9307 0.01694 0.00680 -0.0832 0.3930 1.0000
4.500 0.9550 0.01730 0.00711 -0.0826 0.3830 1.0000
4.750 0.9790 0.01769 0.00741 -0.0819 0.3740 1.0000
5.000 1.0029 0.01805 0.00778 -0.0811 0.3637 1.0000
5.250 1.0265 0.01845 0.00815 -0.0804 0.3542 1.0000
5.500 1.0499 0.01885 0.00852 -0.0796 0.3448 1.0000
5.750 1.0733 0.01923 0.00896 -0.0789 0.3352 1.0000
6.000 1.0962 0.01966 0.00935 -0.0780 0.3263 1.0000
6.250 1.1194 0.02004 0.00982 -0.0772 0.3168 1.0000
6.500 1.1420 0.02047 0.01029 -0.0764 0.3083 1.0000
6.750 1.1642 0.02087 0.01077 -0.0755 0.2981 1.0000
7.000 1.1863 0.02127 0.01128 -0.0745 0.2879 1.0000
7.250 1.2076 0.02170 0.01176 -0.0735 0.2779 1.0000
7.500 1.2283 0.02210 0.01227 -0.0723 0.2656 1.0000
7.750 1.2488 0.02250 0.01279 -0.0712 0.2520 1.0000
8.000 1.2688 0.02295 0.01332 -0.0700 0.2383 1.0000
8.250 1.2882 0.02344 0.01390 -0.0687 0.2249 1.0000
8.500 1.3066 0.02400 0.01453 -0.0673 0.2113 1.0000
8.750 1.3235 0.02465 0.01520 -0.0657 0.1978 1.0000
9.000 1.3389 0.02542 0.01597 -0.0640 0.1852 1.0000
9.250 1.3532 0.02629 0.01687 -0.0621 0.1734 1.0000
9.500 1.3658 0.02728 0.01790 -0.0601 0.1631 1.0000
9.750 1.3778 0.02830 0.01898 -0.0580 0.1532 1.0000
10.000 1.3894 0.02929 0.02010 -0.0558 0.1449 1.0000
10.250 1.3987 0.03035 0.02125 -0.0534 0.1377 1.0000
10.500 1.4090 0.03142 0.02246 -0.0511 0.1316 1.0000
10.750 1.4181 0.03252 0.02371 -0.0489 0.1258 1.0000
11.000 1.4258 0.03369 0.02497 -0.0466 0.1204 1.0000
11.250 1.4332 0.03484 0.02627 -0.0444 0.1137 1.0000
11.500 1.4382 0.03616 0.02767 -0.0423 0.1076 1.0000
11.750 1.4417 0.03765 0.02924 -0.0403 0.1016 1.0000
12.000 1.4432 0.03938 0.03104 -0.0383 0.0972 1.0000
12.250 1.4452 0.04122 0.03306 -0.0366 0.0932 1.0000
12.500 1.4432 0.04344 0.03535 -0.0351 0.0895 1.0000
12.750 1.4403 0.04591 0.03789 -0.0338 0.0861 1.0000
13.000 1.4391 0.04843 0.04065 -0.0329 0.0819 1.0000
13.250 1.4342 0.05144 0.04380 -0.0323 0.0784 1.0000
13.500 1.4263 0.05493 0.04735 -0.0321 0.0755 1.0000
13.750 1.4214 0.05844 0.05110 -0.0324 0.0719 1.0000
14.000 1.4147 0.06240 0.05532 -0.0332 0.0680 1.0000
14.250 1.4046 0.06700 0.06010 -0.0345 0.0648 1.0000
14.500 1.3918 0.07217 0.06537 -0.0363 0.0623 1.0000
14.750 1.3831 0.07719 0.07070 -0.0382 0.0587 1.0000
15.000 1.3708 0.08297 0.07670 -0.0406 0.0551 1.0000
15.250 1.3559 0.08933 0.08321 -0.0436 0.0525 1.0000
15.500 1.3417 0.09581 0.08985 -0.0466 0.0496 1.0000
15.750 1.3281 0.10236 0.09660 -0.0497 0.0463 1.0000
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Polar data table (+)
Polar graphs
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