GOE 187 (SCHTTE-LANZ 2U10) AIRFOIL (goe187-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 187 (SCHTTE-LANZ 2U10) AIRFOIL (goe187-il) Reynolds number: 50,000 Max Cl/Cd: 40.29 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe187-il-50000-n5.txt Download as CSV file: xf-goe187-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 187 (SCHTTE-LANZ 2U10) 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 -0.3098 0.10560 0.09926 -0.0248 1.0000 0.0579
-7.750 -0.3113 0.10398 0.09777 -0.0265 1.0000 0.0590
-7.500 -0.3108 0.10241 0.09632 -0.0298 1.0000 0.0597
-7.250 -0.3076 0.10067 0.09468 -0.0338 1.0000 0.0601
-6.750 -0.2972 0.09210 0.08629 -0.0297 1.0000 0.0630
-6.500 -0.2938 0.08926 0.08354 -0.0292 1.0000 0.0652
-6.250 -0.2914 0.08678 0.08115 -0.0295 1.0000 0.0675
-6.000 -0.2896 0.08455 0.07901 -0.0304 1.0000 0.0700
-5.750 -0.2864 0.08301 0.07751 -0.0334 1.0000 0.0730
-5.500 -0.2783 0.08230 0.07671 -0.0385 1.0000 0.0742
-5.250 -0.2832 0.07795 0.07253 -0.0336 1.0000 0.0760
-5.000 -0.2767 0.07487 0.06951 -0.0324 0.9977 0.0805
-4.750 -0.2369 0.07041 0.06490 -0.0422 0.9880 0.0909
-4.500 -0.2023 0.06629 0.06065 -0.0489 0.9788 0.1051
-4.250 -0.1737 0.06228 0.05660 -0.0528 0.9696 0.1216
-4.000 -0.1404 0.05870 0.05288 -0.0584 0.9599 0.1491
-3.750 -0.1130 0.05509 0.04925 -0.0609 0.9513 0.1813
-2.750 0.0933 0.04044 0.03256 -0.0839 0.9144 0.0727
-2.500 0.1357 0.03769 0.02928 -0.0861 0.9030 0.0590
-2.250 0.1740 0.03492 0.02618 -0.0882 0.8919 0.0567
-2.000 0.2137 0.03258 0.02339 -0.0899 0.8816 0.0537
-1.750 0.2520 0.03066 0.02096 -0.0908 0.8706 0.0498
-1.500 0.2870 0.02933 0.01908 -0.0909 0.8582 0.0477
-1.250 0.3198 0.02777 0.01719 -0.0911 0.8459 0.0483
-1.000 0.3508 0.02643 0.01563 -0.0911 0.8334 0.0528
-0.750 0.3824 0.02536 0.01424 -0.0907 0.8211 0.0550
-0.500 0.4140 0.02442 0.01297 -0.0903 0.8088 0.0571
-0.250 0.4439 0.02356 0.01189 -0.0899 0.7963 0.0653
0.000 0.4735 0.02295 0.01100 -0.0895 0.7837 0.0730
0.250 0.5023 0.02238 0.01026 -0.0891 0.7704 0.0846
0.500 0.5312 0.02148 0.00978 -0.0892 0.7567 0.1824
1.000 0.5853 0.01993 0.00910 -0.0874 0.7285 1.0000
1.250 0.6117 0.02013 0.00896 -0.0867 0.7140 1.0000
1.500 0.6381 0.02034 0.00892 -0.0861 0.6994 1.0000
1.750 0.6643 0.02058 0.00893 -0.0855 0.6846 1.0000
2.000 0.6903 0.02083 0.00899 -0.0849 0.6698 1.0000
2.250 0.7162 0.02110 0.00910 -0.0843 0.6550 1.0000
2.500 0.7420 0.02140 0.00926 -0.0838 0.6404 1.0000
2.750 0.7676 0.02171 0.00948 -0.0832 0.6259 1.0000
3.000 0.7932 0.02206 0.00974 -0.0827 0.6118 1.0000
3.250 0.8186 0.02242 0.01005 -0.0823 0.5981 1.0000
3.500 0.8438 0.02282 0.01043 -0.0818 0.5848 1.0000
3.750 0.8691 0.02323 0.01082 -0.0814 0.5723 1.0000
4.000 0.8944 0.02365 0.01124 -0.0810 0.5607 1.0000
4.250 0.9203 0.02405 0.01165 -0.0806 0.5503 1.0000
4.500 0.9450 0.02454 0.01219 -0.0802 0.5392 1.0000
4.750 0.9695 0.02508 0.01281 -0.0798 0.5286 1.0000
5.000 0.9949 0.02557 0.01340 -0.0794 0.5195 1.0000
5.250 1.0198 0.02610 0.01402 -0.0790 0.5101 1.0000
5.500 1.0435 0.02670 0.01475 -0.0785 0.4999 1.0000
5.750 1.0677 0.02718 0.01532 -0.0779 0.4892 1.0000
6.000 1.0915 0.02755 0.01581 -0.0771 0.4769 1.0000
6.250 1.1145 0.02792 0.01627 -0.0762 0.4631 1.0000
6.500 1.1370 0.02834 0.01678 -0.0752 0.4492 1.0000
6.750 1.1595 0.02879 0.01741 -0.0743 0.4357 1.0000
7.000 1.1808 0.02931 0.01808 -0.0732 0.4213 1.0000
7.500 1.2206 0.03045 0.01959 -0.0708 0.3907 1.0000
7.750 1.2386 0.03111 0.02047 -0.0694 0.3744 1.0000
8.000 1.2568 0.03180 0.02149 -0.0681 0.3595 1.0000
8.250 1.2749 0.03256 0.02252 -0.0667 0.3454 1.0000
8.500 1.2916 0.03338 0.02364 -0.0652 0.3306 1.0000
8.750 1.3068 0.03427 0.02486 -0.0636 0.3149 1.0000
9.000 1.3183 0.03521 0.02611 -0.0615 0.2959 1.0000
9.250 1.3208 0.03614 0.02715 -0.0585 0.2656 1.0000
9.500 1.3179 0.03745 0.02840 -0.0554 0.2278 1.0000
9.750 1.3152 0.03908 0.02994 -0.0523 0.1995 1.0000
10.000 1.3122 0.04110 0.03188 -0.0497 0.1796 1.0000
10.250 1.3081 0.04355 0.03432 -0.0477 0.1624 1.0000
10.500 1.3011 0.04662 0.03740 -0.0462 0.1393 1.0000
10.750 1.2954 0.04987 0.04087 -0.0454 0.1193 1.0000
11.000 1.2864 0.05374 0.04476 -0.0450 0.1004 1.0000
11.250 1.2733 0.05835 0.04931 -0.0452 0.0862 1.0000
11.500 1.2625 0.06297 0.05401 -0.0456 0.0717 1.0000
11.750 1.2530 0.06763 0.05879 -0.0462 0.0485 1.0000
12.000 1.2389 0.07301 0.06413 -0.0474 0.0407 1.0000
12.250 1.2258 0.07842 0.06954 -0.0486 0.0369 1.0000
12.500 1.2144 0.08370 0.07490 -0.0498 0.0344 1.0000
12.750 1.2032 0.08907 0.08037 -0.0512 0.0323 1.0000
13.000 1.1922 0.09451 0.08589 -0.0526 0.0308 1.0000
13.250 1.1814 0.10006 0.09151 -0.0543 0.0296 1.0000
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Polar data table (+)
Polar graphs
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