GOE 363 AIRFOIL (goe363-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 363 AIRFOIL (goe363-il) Reynolds number: 100,000 Max Cl/Cd: 52.28 at α=3.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe363-il-100000-n5.txt Download as CSV file: xf-goe363-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 363 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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.2477 0.11483 0.11029 -0.0333 1.0000 0.0481
-9.250 -0.2542 0.11345 0.10898 -0.0314 1.0000 0.0495
-9.000 -0.2629 0.11220 0.10781 -0.0295 0.9998 0.0511
-8.750 -0.2583 0.10925 0.10489 -0.0381 0.9924 0.0544
-8.500 -0.2502 0.10564 0.10130 -0.0457 0.9849 0.0548
-8.250 -0.2363 0.10067 0.09636 -0.0476 0.9797 0.0554
-8.000 -0.2141 0.09632 0.09199 -0.0480 0.9769 0.0565
-7.750 -0.1991 0.09248 0.08815 -0.0515 0.9704 0.0570
-7.500 -0.1859 0.08630 0.08192 -0.0567 0.9635 0.0411
-7.250 -0.1723 0.08203 0.07765 -0.0616 0.9543 0.0407
-7.000 -0.1511 0.07682 0.07241 -0.0696 0.9482 0.0413
-6.750 -0.1377 0.07241 0.06798 -0.0747 0.9375 0.0412
-6.500 -0.1172 0.06732 0.06283 -0.0812 0.9300 0.0405
-6.250 -0.0988 0.06222 0.05765 -0.0871 0.9211 0.0400
-6.000 -0.0765 0.05655 0.05185 -0.0939 0.9140 0.0405
-5.750 -0.0531 0.04947 0.04451 -0.1014 0.9059 0.0420
-5.500 -0.0248 0.04074 0.03527 -0.1089 0.9004 0.0424
-5.000 0.0274 0.03157 0.02501 -0.1145 0.8884 0.0461
-4.750 0.0525 0.02925 0.02229 -0.1150 0.8817 0.0476
-4.500 0.0819 0.02717 0.01979 -0.1159 0.8763 0.0495
-4.250 0.1154 0.02531 0.01744 -0.1172 0.8726 0.0527
-4.000 0.1406 0.02397 0.01571 -0.1167 0.8650 0.0540
-3.750 0.1722 0.02266 0.01411 -0.1172 0.8600 0.0553
-3.500 0.2008 0.02179 0.01320 -0.1173 0.8539 0.0581
-3.250 0.2291 0.02114 0.01244 -0.1172 0.8471 0.0615
-3.000 0.2621 0.02029 0.01142 -0.1177 0.8425 0.0642
-2.750 0.2875 0.01974 0.01074 -0.1169 0.8326 0.0665
-2.500 0.3174 0.01904 0.01002 -0.1168 0.8232 0.0703
-2.250 0.3479 0.01840 0.00930 -0.1165 0.8121 0.0770
-2.000 0.3747 0.01791 0.00884 -0.1157 0.7977 0.0892
-1.750 0.4015 0.01749 0.00846 -0.1148 0.7824 0.1125
-1.500 0.4280 0.01726 0.00816 -0.1140 0.7676 0.1424
-1.250 0.4542 0.01710 0.00789 -0.1132 0.7534 0.1637
-1.000 0.4804 0.01691 0.00774 -0.1127 0.7399 0.1862
-0.750 0.5066 0.01678 0.00760 -0.1121 0.7257 0.2113
-0.500 0.5324 0.01661 0.00747 -0.1114 0.7104 0.2345
-0.250 0.5585 0.01645 0.00730 -0.1107 0.6939 0.2561
0.000 0.5851 0.01627 0.00708 -0.1102 0.6765 0.2769
0.250 0.6121 0.01607 0.00686 -0.1097 0.6583 0.3079
0.500 0.6386 0.01577 0.00669 -0.1092 0.6389 0.3742
1.000 0.6917 0.01455 0.00638 -0.1074 0.5973 1.0000
1.250 0.7173 0.01475 0.00631 -0.1067 0.5759 1.0000
1.500 0.7424 0.01499 0.00629 -0.1060 0.5550 1.0000
1.750 0.7672 0.01528 0.00633 -0.1052 0.5349 1.0000
2.000 0.7917 0.01559 0.00643 -0.1045 0.5153 1.0000
2.250 0.8159 0.01592 0.00658 -0.1037 0.4954 1.0000
2.500 0.8398 0.01625 0.00676 -0.1029 0.4750 1.0000
2.750 0.8631 0.01662 0.00695 -0.1021 0.4537 1.0000
3.000 0.8863 0.01698 0.00717 -0.1012 0.4306 1.0000
3.250 0.9087 0.01738 0.00739 -0.1003 0.4077 1.0000
3.500 0.9309 0.01781 0.00764 -0.0993 0.3862 1.0000
3.750 0.9528 0.01828 0.00793 -0.0984 0.3674 1.0000
4.000 0.9747 0.01877 0.00825 -0.0974 0.3516 1.0000
4.250 0.9968 0.01926 0.00860 -0.0966 0.3384 1.0000
4.500 1.0189 0.01976 0.00898 -0.0957 0.3276 1.0000
4.750 1.0414 0.02024 0.00938 -0.0950 0.3189 1.0000
5.000 1.0643 0.02071 0.00980 -0.0942 0.3122 1.0000
5.250 1.0872 0.02119 0.01026 -0.0936 0.3059 1.0000
5.500 1.1093 0.02173 0.01071 -0.0928 0.3003 1.0000
5.750 1.1323 0.02218 0.01120 -0.0921 0.2938 1.0000
6.000 1.1540 0.02271 0.01170 -0.0913 0.2877 1.0000
6.250 1.1761 0.02323 0.01221 -0.0905 0.2822 1.0000
6.500 1.1982 0.02373 0.01276 -0.0898 0.2767 1.0000
6.750 1.2195 0.02428 0.01330 -0.0890 0.2718 1.0000
7.000 1.2411 0.02485 0.01388 -0.0882 0.2676 1.0000
7.250 1.2628 0.02538 0.01451 -0.0874 0.2629 1.0000
7.500 1.2837 0.02594 0.01513 -0.0865 0.2583 1.0000
7.750 1.3041 0.02656 0.01577 -0.0856 0.2543 1.0000
8.000 1.3247 0.02716 0.01645 -0.0848 0.2501 1.0000
8.250 1.3443 0.02777 0.01719 -0.0838 0.2455 1.0000
8.500 1.3632 0.02841 0.01789 -0.0827 0.2411 1.0000
9.000 1.3977 0.02976 0.01944 -0.0800 0.2321 1.0000
9.250 1.4102 0.03043 0.02021 -0.0781 0.2254 1.0000
9.500 1.4203 0.03117 0.02100 -0.0760 0.2179 1.0000
9.750 1.4289 0.03195 0.02191 -0.0738 0.2090 1.0000
10.000 1.4387 0.03284 0.02287 -0.0719 0.2018 1.0000
10.250 1.4490 0.03376 0.02396 -0.0702 0.1943 1.0000
10.500 1.4586 0.03478 0.02507 -0.0686 0.1875 1.0000
10.750 1.4675 0.03587 0.02629 -0.0670 0.1788 1.0000
11.000 1.4758 0.03707 0.02762 -0.0655 0.1683 1.0000
11.250 1.4828 0.03844 0.02906 -0.0641 0.1579 1.0000
11.500 1.4872 0.04007 0.03071 -0.0626 0.1473 1.0000
11.750 1.4886 0.04205 0.03270 -0.0612 0.1379 1.0000
12.000 1.4907 0.04410 0.03481 -0.0599 0.1305 1.0000
12.250 1.4894 0.04657 0.03730 -0.0587 0.1244 1.0000
12.500 1.4875 0.04921 0.04002 -0.0576 0.1165 1.0000
12.750 1.4800 0.05255 0.04340 -0.0568 0.1093 1.0000
13.000 1.4779 0.05550 0.04650 -0.0562 0.1011 1.0000
13.250 1.4728 0.05890 0.05004 -0.0558 0.0941 1.0000
13.750 1.4389 0.06942 0.06066 -0.0569 0.0503 1.0000
14.000 1.4161 0.07608 0.06740 -0.0585 0.0393 1.0000
14.250 1.3937 0.08309 0.07456 -0.0605 0.0331 1.0000
14.500 1.3714 0.09036 0.08201 -0.0628 0.0312 1.0000
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Polar data table (+)
Polar graphs
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