GOE 286 AIRFOIL (goe286-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: GOE 286 AIRFOIL (goe286-il) Reynolds number: 50,000 Max Cl/Cd: 37.61 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe286-il-50000-n5.txt Download as CSV file: xf-goe286-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 286 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
------ -------- --------- --------- -------- -------- --------
-7.750 -0.3584 0.09720 0.09067 -0.0197 1.0000 0.1218
-7.500 -0.3625 0.09501 0.08858 -0.0235 1.0000 0.1263
-7.250 -0.3688 0.09330 0.08691 -0.0326 1.0000 0.1282
-7.000 -0.3544 0.08816 0.08187 -0.0271 1.0000 0.1305
-6.750 -0.3454 0.08509 0.07885 -0.0257 1.0000 0.1359
-6.500 -0.3501 0.08359 0.07732 -0.0345 1.0000 0.1437
-6.250 -0.3404 0.07930 0.07317 -0.0289 1.0000 0.1473
-6.000 -0.3347 0.07662 0.07054 -0.0282 1.0000 0.1529
-5.750 -0.3327 0.07394 0.06785 -0.0322 1.0000 0.1610
-5.500 -0.3263 0.07095 0.06493 -0.0300 1.0000 0.1637
-5.000 -0.2850 0.05845 0.05163 -0.0418 1.0000 0.0812
-4.750 -0.2734 0.05556 0.04865 -0.0418 1.0000 0.0806
-4.500 -0.2599 0.05274 0.04567 -0.0421 1.0000 0.0805
-4.250 -0.2245 0.04888 0.04154 -0.0465 0.9926 0.0793
-4.000 -0.1829 0.04493 0.03724 -0.0517 0.9835 0.0769
-3.750 -0.1386 0.04121 0.03303 -0.0568 0.9738 0.0750
-3.500 -0.0937 0.03799 0.02929 -0.0613 0.9626 0.0743
-3.250 -0.0491 0.03552 0.02635 -0.0653 0.9503 0.0767
-3.000 -0.0051 0.03321 0.02355 -0.0687 0.9373 0.0779
-2.750 0.0364 0.03116 0.02107 -0.0714 0.9237 0.0780
-2.500 0.0751 0.02946 0.01899 -0.0732 0.9092 0.0785
-2.250 0.1120 0.02801 0.01718 -0.0745 0.8944 0.0795
-2.000 0.1479 0.02680 0.01564 -0.0754 0.8795 0.0813
-1.750 0.1820 0.02570 0.01445 -0.0761 0.8643 0.0853
-1.500 0.2148 0.02485 0.01346 -0.0764 0.8489 0.0900
-1.250 0.2478 0.02405 0.01245 -0.0764 0.8333 0.0939
-1.000 0.2790 0.02334 0.01157 -0.0762 0.8173 0.0982
-0.750 0.3082 0.02272 0.01088 -0.0758 0.8007 0.1051
-0.500 0.3365 0.02220 0.01029 -0.0752 0.7837 0.1172
-0.250 0.3641 0.02163 0.00978 -0.0747 0.7664 0.1481
0.000 0.3950 0.01865 0.00928 -0.0745 0.7497 1.0000
0.250 0.4215 0.01878 0.00895 -0.0736 0.7316 1.0000
0.500 0.4473 0.01893 0.00878 -0.0727 0.7128 1.0000
0.750 0.4734 0.01908 0.00865 -0.0718 0.6952 1.0000
1.000 0.4995 0.01925 0.00855 -0.0710 0.6781 1.0000
1.250 0.5256 0.01945 0.00851 -0.0702 0.6614 1.0000
1.500 0.5516 0.01970 0.00853 -0.0694 0.6453 1.0000
1.750 0.5776 0.01999 0.00861 -0.0687 0.6295 1.0000
2.000 0.6038 0.02031 0.00875 -0.0681 0.6133 1.0000
2.250 0.6297 0.02066 0.00895 -0.0675 0.5971 1.0000
2.500 0.6555 0.02103 0.00918 -0.0670 0.5811 1.0000
2.750 0.6811 0.02139 0.00944 -0.0664 0.5654 1.0000
3.000 0.7066 0.02176 0.00974 -0.0659 0.5502 1.0000
3.250 0.7320 0.02213 0.01005 -0.0654 0.5357 1.0000
3.500 0.7573 0.02250 0.01037 -0.0650 0.5222 1.0000
3.750 0.7827 0.02288 0.01071 -0.0645 0.5098 1.0000
4.000 0.8083 0.02323 0.01100 -0.0640 0.4985 1.0000
4.250 0.8335 0.02363 0.01140 -0.0635 0.4870 1.0000
4.500 0.8585 0.02406 0.01186 -0.0631 0.4758 1.0000
4.750 0.8837 0.02447 0.01224 -0.0626 0.4658 1.0000
5.000 0.9087 0.02489 0.01266 -0.0621 0.4556 1.0000
5.250 0.9332 0.02540 0.01325 -0.0616 0.4455 1.0000
5.500 0.9588 0.02584 0.01365 -0.0611 0.4379 1.0000
5.750 0.9828 0.02648 0.01445 -0.0608 0.4289 1.0000
6.000 1.0080 0.02697 0.01496 -0.0603 0.4211 1.0000
6.250 1.0313 0.02762 0.01576 -0.0598 0.4115 1.0000
6.500 1.0554 0.02819 0.01640 -0.0592 0.4030 1.0000
6.750 1.0786 0.02879 0.01712 -0.0586 0.3933 1.0000
7.000 1.1004 0.02941 0.01790 -0.0579 0.3820 1.0000
7.250 1.1222 0.02994 0.01852 -0.0570 0.3701 1.0000
7.500 1.1442 0.03042 0.01904 -0.0561 0.3586 1.0000
7.750 1.1636 0.03114 0.01997 -0.0551 0.3462 1.0000
8.000 1.1829 0.03185 0.02090 -0.0541 0.3344 1.0000
8.250 1.2026 0.03253 0.02173 -0.0531 0.3234 1.0000
8.500 1.2221 0.03318 0.02251 -0.0520 0.3125 1.0000
8.750 1.2386 0.03411 0.02370 -0.0508 0.3005 1.0000
9.000 1.2550 0.03504 0.02488 -0.0496 0.2889 1.0000
9.250 1.2705 0.03593 0.02595 -0.0482 0.2770 1.0000
9.500 1.2847 0.03682 0.02697 -0.0466 0.2648 1.0000
9.750 1.2961 0.03795 0.02831 -0.0450 0.2518 1.0000
10.000 1.3060 0.03926 0.02983 -0.0433 0.2396 1.0000
10.250 1.3154 0.04059 0.03135 -0.0416 0.2292 1.0000
10.500 1.3237 0.04185 0.03272 -0.0397 0.2198 1.0000
10.750 1.3259 0.04364 0.03472 -0.0375 0.2103 1.0000
11.000 1.3280 0.04534 0.03652 -0.0355 0.2015 1.0000
11.250 1.3267 0.04739 0.03868 -0.0338 0.1918 1.0000
11.500 1.3230 0.04997 0.04141 -0.0325 0.1822 1.0000
11.750 1.3194 0.05262 0.04412 -0.0317 0.1735 1.0000
12.000 1.3141 0.05563 0.04718 -0.0312 0.1645 1.0000
12.250 1.3060 0.05933 0.05100 -0.0313 0.1557 1.0000
12.500 1.2984 0.06302 0.05471 -0.0315 0.1474 1.0000
12.750 1.2904 0.06690 0.05859 -0.0320 0.1391 1.0000
13.000 1.2807 0.07134 0.06312 -0.0328 0.1315 1.0000
13.250 1.2746 0.07500 0.06667 -0.0331 0.1235 1.0000
13.500 1.2616 0.08038 0.07229 -0.0347 0.1168 1.0000
13.750 1.2543 0.08443 0.07629 -0.0354 0.1092 1.0000
14.000 1.2391 0.09057 0.08273 -0.0376 0.1031 1.0000
14.250 1.2289 0.09560 0.08784 -0.0393 0.0961 1.0000
14.500 1.2117 0.10271 0.09527 -0.0423 0.0905 1.0000
14.750 1.1996 0.10877 0.10147 -0.0448 0.0847 1.0000
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Polar data table (+)
Polar graphs
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