GOE 379 AIRFOIL (goe379-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: GOE 379 AIRFOIL (goe379-il) Reynolds number: 100,000 Max Cl/Cd: 58.22 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe379-il-100000.txt Download as CSV file: xf-goe379-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 379 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-6.500 -0.3103 0.08978 0.08560 -0.0297 1.0000 0.0502
-6.250 -0.3102 0.08572 0.08161 -0.0257 1.0000 0.0510
-6.000 -0.3121 0.08306 0.07901 -0.0232 1.0000 0.0521
-5.750 -0.3149 0.08096 0.07697 -0.0214 1.0000 0.0530
-5.500 -0.3174 0.07902 0.07508 -0.0201 1.0000 0.0540
-5.250 -0.3183 0.07705 0.07314 -0.0193 1.0000 0.0551
-5.000 -0.3172 0.07500 0.07112 -0.0189 1.0000 0.0565
-4.750 -0.3132 0.07287 0.06900 -0.0193 1.0000 0.0583
-4.500 -0.3039 0.07085 0.06694 -0.0209 1.0000 0.0606
-4.000 -0.2409 0.06285 0.05874 -0.0327 0.9905 0.0653
-3.750 -0.2030 0.05885 0.05462 -0.0381 0.9834 0.0724
-3.500 -0.1524 0.05492 0.05041 -0.0468 0.9741 0.0784
-3.250 -0.1181 0.05090 0.04634 -0.0506 0.9669 0.0843
-3.000 -0.0697 0.04738 0.04250 -0.0571 0.9579 0.0926
-2.750 -0.0231 0.04550 0.04018 -0.0620 0.9480 0.1046
-2.500 0.0116 0.04079 0.03553 -0.0653 0.9420 0.1126
-2.000 0.0882 0.03579 0.03002 -0.0712 0.9209 0.1610
-1.750 0.1329 0.03269 0.02681 -0.0749 0.9144 0.1978
-1.250 0.2345 0.02638 0.01895 -0.0790 0.8972 0.1022
-1.000 0.2757 0.02377 0.01584 -0.0803 0.8883 0.0981
-0.750 0.3126 0.02203 0.01359 -0.0807 0.8775 0.1060
-0.500 0.3502 0.02052 0.01183 -0.0817 0.8672 0.1202
-0.250 0.3899 0.01924 0.01046 -0.0831 0.8583 0.1388
0.000 0.4218 0.01840 0.00954 -0.0831 0.8453 0.1542
0.250 0.4527 0.01764 0.00874 -0.0829 0.8320 0.1697
0.500 0.4856 0.01696 0.00804 -0.0831 0.8184 0.1891
0.750 0.5150 0.01632 0.00749 -0.0828 0.8043 0.2363
1.000 0.5951 0.01418 0.00661 -0.0930 0.7907 1.0000
1.250 0.6204 0.01424 0.00644 -0.0918 0.7752 1.0000
1.500 0.6440 0.01437 0.00642 -0.0905 0.7581 1.0000
1.750 0.6679 0.01450 0.00640 -0.0892 0.7410 1.0000
2.000 0.6921 0.01463 0.00642 -0.0880 0.7246 1.0000
2.250 0.7166 0.01477 0.00643 -0.0869 0.7084 1.0000
2.500 0.7412 0.01492 0.00645 -0.0858 0.6924 1.0000
2.750 0.7650 0.01512 0.00656 -0.0847 0.6756 1.0000
3.000 0.7886 0.01536 0.00673 -0.0836 0.6586 1.0000
3.250 0.8126 0.01560 0.00694 -0.0826 0.6420 1.0000
3.500 0.8367 0.01585 0.00712 -0.0816 0.6260 1.0000
3.750 0.8609 0.01612 0.00731 -0.0806 0.6101 1.0000
4.000 0.8851 0.01639 0.00750 -0.0796 0.5943 1.0000
4.250 0.9077 0.01671 0.00780 -0.0785 0.5766 1.0000
4.500 0.9308 0.01703 0.00816 -0.0774 0.5601 1.0000
4.750 0.9543 0.01740 0.00853 -0.0764 0.5453 1.0000
5.000 0.9780 0.01782 0.00898 -0.0756 0.5318 1.0000
5.250 1.0016 0.01827 0.00947 -0.0747 0.5190 1.0000
5.500 1.0254 0.01875 0.01001 -0.0739 0.5069 1.0000
5.750 1.0495 0.01924 0.01060 -0.0731 0.4955 1.0000
6.000 1.0733 0.01972 0.01117 -0.0723 0.4837 1.0000
6.250 1.0927 0.01985 0.01141 -0.0705 0.4625 1.0000
6.500 1.1100 0.01963 0.01117 -0.0681 0.4340 1.0000
6.750 1.1306 0.01983 0.01144 -0.0665 0.4156 1.0000
7.000 1.1445 0.01973 0.01140 -0.0637 0.3815 1.0000
7.250 1.1579 0.01989 0.01162 -0.0608 0.3431 1.0000
7.500 1.1665 0.02045 0.01202 -0.0574 0.2697 1.0000
7.750 1.1606 0.02304 0.01339 -0.0528 0.0966 1.0000
8.000 1.1594 0.02569 0.01556 -0.0489 0.0565 1.0000
8.250 1.1684 0.02720 0.01720 -0.0461 0.0492 1.0000
8.500 1.1724 0.02894 0.01908 -0.0428 0.0454 1.0000
8.750 1.1726 0.03071 0.02101 -0.0390 0.0436 1.0000
9.000 1.1732 0.03225 0.02272 -0.0352 0.0426 1.0000
9.250 1.1734 0.03398 0.02458 -0.0317 0.0415 1.0000
9.500 1.1771 0.03578 0.02646 -0.0288 0.0408 1.0000
9.750 1.1867 0.03765 0.02844 -0.0265 0.0395 1.0000
10.000 1.1983 0.03974 0.03051 -0.0247 0.0362 1.0000
10.250 1.2360 0.04256 0.03334 -0.0250 0.0353 1.0000
10.500 1.2783 0.04612 0.03720 -0.0262 0.0360 1.0000
10.750 1.3022 0.04979 0.04134 -0.0253 0.0378 1.0000
11.000 1.3103 0.05353 0.04556 -0.0230 0.0396 1.0000
11.250 1.3134 0.05757 0.04998 -0.0206 0.0413 1.0000
11.500 1.3188 0.06298 0.05567 -0.0192 0.0432 1.0000
11.750 1.3228 0.06538 0.05843 -0.0162 0.0461 1.0000
12.000 1.2944 0.06783 0.06128 -0.0119 0.0471 1.0000
12.250 1.2701 0.07129 0.06509 -0.0097 0.0481 1.0000
12.500 1.2475 0.07549 0.06957 -0.0088 0.0490 1.0000
12.750 1.2243 0.08034 0.07467 -0.0091 0.0498 1.0000
13.000 1.2012 0.08564 0.08018 -0.0104 0.0503 1.0000
13.250 1.1771 0.09150 0.08624 -0.0127 0.0506 1.0000
13.500 1.1534 0.09776 0.09266 -0.0161 0.0505 1.0000
13.750 1.1281 0.10490 0.09995 -0.0205 0.0502 1.0000
14.000 1.1032 0.11273 0.10789 -0.0257 0.0497 1.0000
14.250 1.0772 0.12179 0.11705 -0.0320 0.0493 1.0000
14.500 1.0508 0.13236 0.12768 -0.0393 0.0491 1.0000
14.750 1.0225 0.14565 0.14095 -0.0478 0.0501 1.0000
15.000 1.0104 0.15555 0.15080 -0.0527 0.0529 1.0000
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Polar data table (+)
Polar graphs
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