GOE 419 AIRFOIL (goe419-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 419 AIRFOIL (goe419-il) Reynolds number: 50,000 Max Cl/Cd: 40.91 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe419-il-50000-n5.txt Download as CSV file: xf-goe419-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 419 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 -0.3700 0.10676 0.10006 -0.0258 1.0000 0.0637
-8.000 -0.3748 0.10560 0.09903 -0.0267 1.0000 0.0645
-7.750 -0.3768 0.10418 0.09773 -0.0286 1.0000 0.0649
-7.500 -0.3752 0.10250 0.09614 -0.0317 1.0000 0.0652
-7.250 -0.3692 0.09736 0.09109 -0.0299 1.0000 0.0661
-7.000 -0.3626 0.09285 0.08661 -0.0274 1.0000 0.0682
-6.750 -0.3583 0.08980 0.08363 -0.0273 1.0000 0.0703
-6.500 -0.3540 0.08701 0.08090 -0.0280 1.0000 0.0722
-6.250 -0.3490 0.08440 0.07835 -0.0294 1.0000 0.0750
-6.000 -0.3394 0.08284 0.07680 -0.0349 1.0000 0.0783
-5.500 -0.3270 0.07572 0.06978 -0.0345 1.0000 0.0809
-5.250 -0.3211 0.07254 0.06664 -0.0333 1.0000 0.0846
-5.000 -0.3012 0.07070 0.06464 -0.0391 1.0000 0.0921
-4.750 -0.2948 0.06676 0.06077 -0.0379 1.0000 0.0945
-4.500 -0.2863 0.06362 0.05764 -0.0368 1.0000 0.1006
-4.250 -0.2667 0.06063 0.05447 -0.0400 1.0000 0.1087
-3.750 -0.2118 0.05169 0.04503 -0.0451 1.0000 0.0544
-3.500 -0.1908 0.04816 0.04132 -0.0459 1.0000 0.0463
-3.250 -0.1534 0.04422 0.03676 -0.0489 1.0000 0.0401
-3.000 -0.1322 0.04099 0.03335 -0.0495 1.0000 0.0393
-2.750 -0.1060 0.03783 0.02984 -0.0504 1.0000 0.0388
-2.250 -0.0336 0.03199 0.02303 -0.0553 0.9925 0.0462
-2.000 0.0078 0.02913 0.01944 -0.0576 0.9879 0.0484
-1.750 0.0460 0.02713 0.01683 -0.0596 0.9819 0.0592
-1.500 0.0838 0.02529 0.01442 -0.0612 0.9760 0.0712
-1.250 0.1239 0.02393 0.01244 -0.0629 0.9704 0.0919
-1.000 0.1605 0.02304 0.01131 -0.0647 0.9626 0.1194
-0.750 0.1982 0.02222 0.01026 -0.0666 0.9548 0.1444
-0.500 0.2366 0.02139 0.00967 -0.0691 0.9456 0.2249
-0.250 0.2769 0.01917 0.00901 -0.0716 0.9362 1.0000
0.000 0.3159 0.01930 0.00861 -0.0738 0.9244 1.0000
0.250 0.3550 0.01941 0.00838 -0.0761 0.9131 1.0000
0.500 0.3962 0.01948 0.00821 -0.0788 0.9033 1.0000
0.750 0.4314 0.01959 0.00816 -0.0803 0.8914 1.0000
1.000 0.4670 0.01970 0.00817 -0.0819 0.8799 1.0000
1.250 0.5020 0.01981 0.00823 -0.0833 0.8682 1.0000
1.500 0.5361 0.01991 0.00832 -0.0844 0.8563 1.0000
1.750 0.5695 0.02002 0.00849 -0.0854 0.8440 1.0000
2.000 0.6017 0.02013 0.00868 -0.0861 0.8310 1.0000
2.250 0.6327 0.02026 0.00891 -0.0865 0.8174 1.0000
2.500 0.6625 0.02041 0.00929 -0.0866 0.8029 1.0000
2.750 0.6912 0.02057 0.00964 -0.0866 0.7878 1.0000
3.000 0.7193 0.02074 0.01005 -0.0863 0.7720 1.0000
3.250 0.7472 0.02092 0.01051 -0.0860 0.7559 1.0000
3.500 0.7755 0.02108 0.01112 -0.0855 0.7396 1.0000
3.750 0.7983 0.01961 0.00951 -0.0798 0.6503 1.0000
4.000 0.8091 0.01978 0.00889 -0.0739 0.4946 1.0000
4.250 0.8170 0.02128 0.00926 -0.0697 0.3103 1.0000
4.500 0.8180 0.02506 0.01113 -0.0668 0.0465 1.0000
4.750 0.8360 0.02661 0.01287 -0.0651 0.0385 1.0000
5.000 0.8544 0.02796 0.01465 -0.0633 0.0354 1.0000
5.250 0.8696 0.02958 0.01654 -0.0613 0.0320 1.0000
5.500 0.8819 0.03144 0.01863 -0.0590 0.0295 1.0000
5.750 0.8968 0.03303 0.02049 -0.0568 0.0282 1.0000
6.000 0.9140 0.03479 0.02250 -0.0547 0.0277 1.0000
6.250 0.9387 0.03673 0.02463 -0.0533 0.0274 1.0000
6.500 0.9726 0.03915 0.02724 -0.0529 0.0271 1.0000
6.750 1.0046 0.04189 0.03038 -0.0526 0.0260 1.0000
7.000 1.0310 0.04482 0.03366 -0.0518 0.0252 1.0000
7.250 1.0532 0.04801 0.03730 -0.0504 0.0250 1.0000
7.500 1.0718 0.05135 0.04110 -0.0487 0.0260 1.0000
7.750 1.0859 0.05487 0.04508 -0.0467 0.0271 1.0000
8.000 1.0965 0.05860 0.04921 -0.0447 0.0282 1.0000
8.250 1.1054 0.06288 0.05377 -0.0429 0.0294 1.0000
8.500 1.1136 0.06638 0.05766 -0.0408 0.0313 1.0000
8.750 1.1077 0.06936 0.06127 -0.0373 0.0332 1.0000
9.000 1.1009 0.07314 0.06541 -0.0348 0.0346 1.0000
9.250 1.0925 0.07709 0.06962 -0.0327 0.0358 1.0000
9.500 1.0825 0.08097 0.07368 -0.0307 0.0368 1.0000
9.750 1.0849 0.08542 0.07825 -0.0297 0.0395 1.0000
10.000 1.0640 0.08865 0.08171 -0.0282 0.0398 1.0000
10.250 1.0442 0.09268 0.08591 -0.0283 0.0399 1.0000
10.500 1.0244 0.09745 0.09082 -0.0298 0.0400 1.0000
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Polar data table (+)
Polar graphs
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