GOE 300 (FRIEDRICHSHAFEN G20) AIRFOIL (goe300-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 300 (FRIEDRICHSHAFEN G20) AIRFOIL (goe300-il) Reynolds number: 200,000 Max Cl/Cd: 79.1 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe300-il-200000.txt Download as CSV file: xf-goe300-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 300 (FRIEDRICHSHAFEN G20) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.2534 0.09695 0.09369 -0.0284 1.0000 0.0425
-7.750 -0.2708 0.09668 0.09352 -0.0250 1.0000 0.0430
-7.500 -0.2918 0.09678 0.09373 -0.0216 0.9990 0.0432
-7.250 -0.2571 0.09153 0.08844 -0.0391 0.9884 0.0439
-7.000 -0.2385 0.08673 0.08366 -0.0366 0.9863 0.0447
-6.750 -0.2105 0.08254 0.07945 -0.0417 0.9817 0.0459
-6.500 -0.1808 0.07838 0.07525 -0.0486 0.9744 0.0475
-6.250 -0.1269 0.07391 0.07063 -0.0681 0.9649 0.0508
-6.000 -0.0936 0.06836 0.06500 -0.0759 0.9582 0.0514
-5.750 -0.0755 0.06451 0.06121 -0.0748 0.9527 0.0524
-5.500 -0.0499 0.06137 0.05804 -0.0775 0.9432 0.0544
-5.250 -0.0200 0.05807 0.05465 -0.0823 0.9318 0.0573
-5.000 0.0289 0.05407 0.05027 -0.0936 0.9191 0.0601
-4.750 0.0423 0.05061 0.04687 -0.0922 0.9081 0.0610
-4.500 0.0582 0.04834 0.04458 -0.0912 0.8940 0.0628
-4.250 0.0813 0.04606 0.04218 -0.0921 0.8796 0.0661
-4.000 0.1233 0.04311 0.03874 -0.0973 0.8654 0.0708
-3.750 0.1385 0.04025 0.03591 -0.0962 0.8512 0.0720
-3.500 0.1583 0.03834 0.03394 -0.0956 0.8372 0.0748
-3.250 0.2001 0.03724 0.03220 -0.0981 0.8235 0.0828
-3.000 0.2173 0.03382 0.02881 -0.0977 0.8095 0.0843
-2.750 0.2385 0.03208 0.02703 -0.0972 0.7943 0.0874
-2.500 0.2740 0.03098 0.02539 -0.0981 0.7801 0.0968
-2.250 0.2952 0.02859 0.02301 -0.0980 0.7667 0.0989
-2.000 0.3202 0.02733 0.02163 -0.0978 0.7542 0.1047
-1.750 0.3501 0.02588 0.01982 -0.0981 0.7430 0.1126
-1.500 0.3752 0.02464 0.01849 -0.0980 0.7311 0.1178
-1.250 0.4035 0.02353 0.01713 -0.0980 0.7193 0.1279
-1.000 0.4325 0.02304 0.01631 -0.0979 0.7086 0.1402
-0.750 0.4573 0.02159 0.01484 -0.0978 0.6980 0.1455
-0.500 0.4843 0.02077 0.01388 -0.0977 0.6868 0.1591
-0.250 0.4203 0.03068 0.02628 -0.0862 0.6903 0.1372
0.000 0.5380 0.01931 0.01215 -0.0974 0.6670 0.1909
0.250 0.5744 0.01778 0.00993 -0.0966 0.6580 0.1205
0.500 0.6034 0.01683 0.00863 -0.0961 0.6492 0.1128
0.750 0.6305 0.01640 0.00816 -0.0959 0.6391 0.1151
1.000 0.6582 0.01597 0.00757 -0.0955 0.6304 0.1153
1.250 0.6854 0.01559 0.00711 -0.0951 0.6198 0.1159
1.500 0.7125 0.01531 0.00674 -0.0947 0.6092 0.1175
1.750 0.7394 0.01516 0.00646 -0.0942 0.5989 0.1214
2.000 0.7661 0.01503 0.00627 -0.0937 0.5869 0.1242
2.250 0.7923 0.01468 0.00596 -0.0933 0.5756 0.1274
2.500 0.8187 0.01456 0.00580 -0.0929 0.5648 0.1318
2.750 0.8450 0.01451 0.00572 -0.0924 0.5532 0.1380
3.000 0.8708 0.01437 0.00566 -0.0920 0.5414 0.1463
3.250 0.8969 0.01433 0.00561 -0.0915 0.5304 0.1554
3.500 0.9229 0.01432 0.00558 -0.0911 0.5196 0.1684
3.750 0.9487 0.01428 0.00563 -0.0907 0.5075 0.1937
4.000 0.9761 0.01298 0.00572 -0.0905 0.4959 1.0000
4.250 1.0019 0.01322 0.00578 -0.0900 0.4850 1.0000
4.500 1.0275 0.01343 0.00594 -0.0895 0.4737 1.0000
4.750 1.0531 0.01367 0.00615 -0.0891 0.4632 1.0000
5.250 1.1042 0.01417 0.00656 -0.0882 0.4442 1.0000
5.500 1.1295 0.01444 0.00678 -0.0877 0.4350 1.0000
5.750 1.1547 0.01470 0.00703 -0.0873 0.4261 1.0000
6.000 1.1797 0.01497 0.00730 -0.0868 0.4171 1.0000
6.250 1.2046 0.01527 0.00754 -0.0863 0.4086 1.0000
6.500 1.2292 0.01554 0.00789 -0.0858 0.3996 1.0000
6.750 1.2538 0.01589 0.00817 -0.0853 0.3918 1.0000
7.000 1.2779 0.01618 0.00854 -0.0848 0.3824 1.0000
7.250 1.3016 0.01654 0.00890 -0.0841 0.3733 1.0000
7.500 1.3248 0.01690 0.00925 -0.0834 0.3632 1.0000
7.750 1.3476 0.01725 0.00968 -0.0827 0.3525 1.0000
8.000 1.3696 0.01767 0.01010 -0.0819 0.3411 1.0000
8.250 1.3908 0.01814 0.01055 -0.0809 0.3287 1.0000
8.500 1.4109 0.01861 0.01103 -0.0798 0.3147 1.0000
8.750 1.4299 0.01910 0.01155 -0.0785 0.2989 1.0000
9.000 1.4479 0.01963 0.01213 -0.0771 0.2816 1.0000
9.250 1.4653 0.02019 0.01273 -0.0757 0.2640 1.0000
9.500 1.4818 0.02080 0.01335 -0.0741 0.2476 1.0000
9.750 1.4971 0.02147 0.01400 -0.0725 0.2326 1.0000
10.000 1.5110 0.02222 0.01473 -0.0707 0.2195 1.0000
10.250 1.5221 0.02308 0.01553 -0.0685 0.2090 1.0000
10.500 1.5331 0.02393 0.01641 -0.0663 0.1997 1.0000
10.750 1.5427 0.02492 0.01741 -0.0641 0.1915 1.0000
11.000 1.5506 0.02606 0.01852 -0.0618 0.1839 1.0000
11.250 1.5603 0.02716 0.01969 -0.0599 0.1772 1.0000
11.500 1.5677 0.02842 0.02097 -0.0579 0.1705 1.0000
11.750 1.5757 0.02971 0.02232 -0.0561 0.1642 1.0000
12.000 1.5834 0.03100 0.02372 -0.0544 0.1580 1.0000
12.250 1.5891 0.03258 0.02526 -0.0526 0.1522 1.0000
12.500 1.5964 0.03393 0.02684 -0.0513 0.1462 1.0000
12.750 1.6002 0.03566 0.02863 -0.0499 0.1402 1.0000
13.000 1.6054 0.03735 0.03051 -0.0489 0.1335 1.0000
13.250 1.6074 0.03942 0.03268 -0.0480 0.1260 1.0000
13.500 1.6116 0.04148 0.03493 -0.0476 0.1158 1.0000
13.750 1.6111 0.04417 0.03769 -0.0473 0.1020 1.0000
14.000 1.6027 0.04787 0.04137 -0.0471 0.0843 1.0000
14.250 1.5876 0.05246 0.04589 -0.0470 0.0698 1.0000
14.500 1.5717 0.05731 0.05073 -0.0470 0.0607 1.0000
14.750 1.5556 0.06239 0.05583 -0.0474 0.0552 1.0000
15.000 1.5426 0.06722 0.06075 -0.0479 0.0508 1.0000
15.250 1.5263 0.07266 0.06625 -0.0488 0.0482 1.0000
15.500 1.5152 0.07750 0.07120 -0.0496 0.0457 1.0000
15.750 1.5039 0.08247 0.07629 -0.0506 0.0436 1.0000
16.000 1.4914 0.08773 0.08163 -0.0518 0.0420 1.0000
16.250 1.4775 0.09321 0.08715 -0.0531 0.0407 1.0000
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Polar data table (+)
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