GOE 723 AIRFOIL (goe723-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 723 AIRFOIL (goe723-il) Reynolds number: 50,000 Max Cl/Cd: 33.41 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe723-il-50000-n5.txt Download as CSV file: xf-goe723-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 723 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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3477 0.09577 0.08880 -0.0441 1.0000 0.0869
-8.000 -0.3466 0.09367 0.08679 -0.0418 1.0000 0.0861
-7.750 -0.3542 0.09196 0.08519 -0.0392 1.0000 0.0852
-7.500 -0.3687 0.09057 0.08394 -0.0362 1.0000 0.0843
-7.250 -0.3841 0.08909 0.08259 -0.0336 1.0000 0.0833
-6.750 -0.3646 0.07134 0.06461 -0.0587 0.9750 0.0744
-6.500 -0.3439 0.06643 0.05959 -0.0642 0.9644 0.0735
-6.250 -0.3242 0.06087 0.05383 -0.0706 0.9533 0.0726
-6.000 -0.3027 0.05492 0.04756 -0.0774 0.9429 0.0716
-5.750 -0.2780 0.04935 0.04151 -0.0836 0.9334 0.0714
-5.500 -0.2550 0.04524 0.03690 -0.0871 0.9231 0.0721
-5.250 -0.2226 0.04148 0.03251 -0.0911 0.9165 0.0730
-5.000 -0.1983 0.03892 0.02946 -0.0923 0.9064 0.0735
-4.750 -0.1633 0.03640 0.02643 -0.0948 0.9007 0.0738
-4.500 -0.1376 0.03471 0.02435 -0.0952 0.8914 0.0742
-4.250 -0.1024 0.03300 0.02227 -0.0969 0.8854 0.0748
-4.000 -0.0739 0.03168 0.02081 -0.0974 0.8774 0.0759
-3.750 -0.0427 0.03059 0.01960 -0.0982 0.8702 0.0779
-3.500 -0.0087 0.02961 0.01845 -0.0994 0.8645 0.0812
-3.250 0.0160 0.02894 0.01761 -0.0989 0.8550 0.0843
-3.000 0.0520 0.02808 0.01654 -0.1001 0.8497 0.0872
-2.750 0.0750 0.02754 0.01599 -0.0994 0.8403 0.0900
-2.500 0.1083 0.02689 0.01524 -0.1003 0.8342 0.0946
-1.750 0.2019 0.02517 0.01370 -0.1024 0.8133 0.1629
-1.500 0.2266 0.02482 0.01382 -0.1022 0.8044 0.2812
-1.250 0.2586 0.02466 0.01396 -0.1026 0.7989 0.3992
-1.000 0.2768 0.02490 0.01435 -0.1008 0.7895 0.4640
-0.750 0.3047 0.02480 0.01441 -0.1002 0.7834 0.5323
-0.500 0.3265 0.02484 0.01454 -0.0989 0.7751 0.5784
-0.250 0.3560 0.02467 0.01441 -0.0989 0.7685 0.6183
0.000 0.3866 0.02440 0.01424 -0.0990 0.7623 0.6660
0.250 0.4133 0.02415 0.01428 -0.0986 0.7541 0.7429
0.500 0.4729 0.02366 0.01383 -0.1045 0.7491 1.0000
0.750 0.4945 0.02417 0.01412 -0.1037 0.7396 1.0000
1.000 0.5266 0.02432 0.01405 -0.1043 0.7332 1.0000
1.250 0.5486 0.02480 0.01437 -0.1035 0.7240 1.0000
1.500 0.5786 0.02498 0.01439 -0.1036 0.7169 1.0000
1.750 0.6012 0.02543 0.01473 -0.1027 0.7079 1.0000
2.000 0.6297 0.02564 0.01482 -0.1026 0.7003 1.0000
2.250 0.6523 0.02608 0.01518 -0.1017 0.6914 1.0000
2.500 0.6797 0.02632 0.01535 -0.1014 0.6836 1.0000
2.750 0.7020 0.02679 0.01577 -0.1004 0.6748 1.0000
3.000 0.7283 0.02708 0.01601 -0.0999 0.6669 1.0000
3.250 0.7505 0.02756 0.01648 -0.0990 0.6582 1.0000
3.500 0.7759 0.02789 0.01679 -0.0984 0.6502 1.0000
3.750 0.7976 0.02841 0.01732 -0.0973 0.6416 1.0000
4.000 0.8224 0.02876 0.01768 -0.0966 0.6335 1.0000
4.250 0.8430 0.02933 0.01828 -0.0955 0.6246 1.0000
4.500 0.8681 0.02968 0.01866 -0.0948 0.6167 1.0000
4.750 0.8870 0.03034 0.01938 -0.0935 0.6075 1.0000
5.000 0.9129 0.03065 0.01973 -0.0929 0.5998 1.0000
5.250 0.9295 0.03144 0.02060 -0.0913 0.5904 1.0000
5.500 0.9564 0.03171 0.02093 -0.0908 0.5830 1.0000
5.750 0.9705 0.03264 0.02198 -0.0890 0.5731 1.0000
6.000 0.9985 0.03287 0.02228 -0.0886 0.5662 1.0000
6.250 1.0097 0.03397 0.02351 -0.0865 0.5560 1.0000
6.500 1.0401 0.03403 0.02367 -0.0862 0.5493 1.0000
6.750 1.0501 0.03499 0.02476 -0.0838 0.5374 1.0000
7.000 1.0725 0.03495 0.02481 -0.0822 0.5251 1.0000
7.250 1.0958 0.03444 0.02437 -0.0803 0.5094 1.0000
7.500 1.1137 0.03412 0.02411 -0.0777 0.4918 1.0000
7.750 1.1285 0.03403 0.02408 -0.0750 0.4740 1.0000
8.000 1.1406 0.03414 0.02424 -0.0721 0.4562 1.0000
8.250 1.1497 0.03453 0.02472 -0.0690 0.4396 1.0000
8.500 1.1581 0.03498 0.02525 -0.0659 0.4218 1.0000
8.750 1.1654 0.03549 0.02579 -0.0629 0.4012 1.0000
9.000 1.1666 0.03655 0.02692 -0.0597 0.3781 1.0000
9.250 1.1715 0.03744 0.02780 -0.0570 0.3525 1.0000
9.500 1.1739 0.03869 0.02900 -0.0543 0.3233 1.0000
9.750 1.1711 0.04056 0.03084 -0.0518 0.2873 1.0000
10.000 1.1655 0.04288 0.03296 -0.0495 0.2394 1.0000
10.250 1.1560 0.04579 0.03548 -0.0475 0.1927 1.0000
10.500 1.1456 0.04913 0.03847 -0.0459 0.1664 1.0000
10.750 1.1383 0.05239 0.04154 -0.0447 0.1516 1.0000
11.000 1.1331 0.05556 0.04455 -0.0437 0.1422 1.0000
11.250 1.1324 0.05836 0.04734 -0.0427 0.1343 1.0000
11.500 1.1317 0.06114 0.04998 -0.0417 0.1284 1.0000
11.750 1.1366 0.06342 0.05236 -0.0408 0.1221 1.0000
12.000 1.1419 0.06562 0.05458 -0.0398 0.1168 1.0000
12.250 1.1518 0.06735 0.05628 -0.0385 0.1124 1.0000
12.500 1.1644 0.06895 0.05806 -0.0374 0.1081 1.0000
12.750 1.1778 0.07049 0.05966 -0.0362 0.1035 1.0000
13.000 1.2010 0.07109 0.06015 -0.0345 0.0987 1.0000
13.250 1.2139 0.07302 0.06242 -0.0336 0.0953 1.0000
13.500 1.2272 0.07495 0.06456 -0.0328 0.0916 1.0000
13.750 1.2441 0.07648 0.06615 -0.0318 0.0877 1.0000
14.000 1.2604 0.07841 0.06818 -0.0309 0.0844 1.0000
14.250 1.2599 0.08187 0.07197 -0.0308 0.0821 1.0000
14.500 1.2586 0.08542 0.07580 -0.0308 0.0796 1.0000
14.750 1.2601 0.08865 0.07920 -0.0309 0.0772 1.0000
15.000 1.2791 0.09021 0.08070 -0.0300 0.0742 1.0000
15.250 1.2626 0.09554 0.08636 -0.0312 0.0733 1.0000
15.500 1.2443 0.10142 0.09258 -0.0330 0.0724 1.0000
15.750 1.2231 0.10810 0.09956 -0.0356 0.0717 1.0000
16.000 1.1993 0.11569 0.10742 -0.0391 0.0713 1.0000
16.250 1.1699 0.12492 0.11691 -0.0441 0.0712 1.0000
16.500 1.1339 0.13657 0.12877 -0.0511 0.0716 1.0000
16.750 1.0916 0.15166 0.14400 -0.0606 0.0722 1.0000
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Polar data table (+)
Polar graphs
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