GOE 402 AIRFOIL (goe402-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 402 AIRFOIL (goe402-il) Reynolds number: 50,000 Max Cl/Cd: 40.42 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe402-il-50000-n5.txt Download as CSV file: xf-goe402-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 402 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 -0.2637 0.10390 0.09754 -0.0258 1.0000 0.0535
-7.500 -0.2671 0.10273 0.09651 -0.0258 1.0000 0.0542
-7.250 -0.2682 0.10152 0.09544 -0.0272 1.0000 0.0546
-7.000 -0.2671 0.10026 0.09429 -0.0293 1.0000 0.0549
-6.750 -0.2641 0.09885 0.09299 -0.0317 1.0000 0.0552
-6.500 -0.2612 0.09458 0.08885 -0.0296 1.0000 0.0558
-6.250 -0.2588 0.09040 0.08476 -0.0258 1.0000 0.0578
-6.000 -0.2592 0.08814 0.08261 -0.0245 1.0000 0.0602
-5.750 -0.2619 0.08650 0.08108 -0.0237 1.0000 0.0615
-5.500 -0.2665 0.08517 0.07986 -0.0230 1.0000 0.0635
-5.250 -0.2130 0.08237 0.07688 -0.0406 0.9846 0.0682
-5.000 -0.2000 0.07656 0.07115 -0.0385 0.9763 0.0724
-4.750 -0.1547 0.07354 0.06791 -0.0500 0.9619 0.0808
-4.500 -0.1277 0.06872 0.06309 -0.0537 0.9514 0.0841
-4.250 -0.0760 0.06620 0.06027 -0.0652 0.9388 0.0959
-4.000 -0.0634 0.06127 0.05548 -0.0636 0.9277 0.1023
-3.750 -0.0291 0.05792 0.05201 -0.0688 0.9162 0.1187
-3.500 0.0081 0.05452 0.04845 -0.0744 0.9060 0.1416
-3.250 0.0450 0.05142 0.04519 -0.0792 0.8963 0.1694
-2.750 0.0995 0.04534 0.03900 -0.0828 0.8741 0.2428
-2.250 0.2216 0.03769 0.02987 -0.0962 0.8555 0.0862
-2.000 0.2625 0.03512 0.02673 -0.0984 0.8432 0.0793
-1.750 0.3005 0.03291 0.02399 -0.0999 0.8301 0.0803
-1.500 0.3353 0.03074 0.02142 -0.1008 0.8162 0.0783
-1.250 0.3695 0.02900 0.01919 -0.1012 0.8020 0.0780
-1.000 0.4019 0.02766 0.01735 -0.1014 0.7880 0.0832
-0.750 0.4335 0.02647 0.01574 -0.1014 0.7748 0.0832
-0.500 0.4635 0.02551 0.01440 -0.1010 0.7622 0.0832
-0.250 0.4939 0.02469 0.01321 -0.1007 0.7498 0.0838
0.000 0.5233 0.02407 0.01230 -0.1002 0.7367 0.0851
0.250 0.5510 0.02359 0.01160 -0.0996 0.7232 0.0872
0.500 0.5778 0.02330 0.01109 -0.0989 0.7097 0.0951
0.750 0.6038 0.02295 0.01067 -0.0983 0.6963 0.1019
1.000 0.6298 0.02274 0.01031 -0.0975 0.6828 0.1060
1.250 0.6559 0.02261 0.01005 -0.0968 0.6693 0.1111
1.500 0.6818 0.02250 0.00988 -0.0962 0.6558 0.1202
1.750 0.7078 0.02238 0.00983 -0.0956 0.6422 0.1429
2.000 0.7351 0.02086 0.00979 -0.0953 0.6286 1.0000
2.250 0.7604 0.02113 0.00976 -0.0944 0.6149 1.0000
2.500 0.7857 0.02140 0.00979 -0.0936 0.6014 1.0000
2.750 0.8109 0.02167 0.00987 -0.0929 0.5881 1.0000
3.000 0.8356 0.02199 0.01006 -0.0921 0.5745 1.0000
3.250 0.8601 0.02235 0.01030 -0.0914 0.5611 1.0000
3.500 0.8845 0.02274 0.01060 -0.0907 0.5482 1.0000
3.750 0.9090 0.02315 0.01097 -0.0900 0.5359 1.0000
4.000 0.9337 0.02357 0.01132 -0.0894 0.5244 1.0000
4.250 0.9591 0.02396 0.01163 -0.0888 0.5143 1.0000
4.500 0.9828 0.02451 0.01220 -0.0882 0.5032 1.0000
4.750 1.0068 0.02509 0.01284 -0.0877 0.4934 1.0000
5.000 1.0323 0.02554 0.01326 -0.0872 0.4854 1.0000
5.250 1.0548 0.02624 0.01407 -0.0865 0.4755 1.0000
5.500 1.0791 0.02683 0.01474 -0.0860 0.4678 1.0000
5.750 1.1022 0.02753 0.01556 -0.0854 0.4598 1.0000
6.000 1.1260 0.02822 0.01633 -0.0849 0.4530 1.0000
6.250 1.1483 0.02899 0.01726 -0.0843 0.4454 1.0000
6.500 1.1715 0.02967 0.01811 -0.0836 0.4383 1.0000
6.750 1.1932 0.03045 0.01907 -0.0829 0.4304 1.0000
7.000 1.2149 0.03118 0.01997 -0.0821 0.4224 1.0000
7.250 1.2375 0.03174 0.02066 -0.0812 0.4137 1.0000
7.500 1.2561 0.03257 0.02177 -0.0801 0.4039 1.0000
7.750 1.2779 0.03310 0.02245 -0.0791 0.3946 1.0000
8.000 1.2985 0.03369 0.02323 -0.0780 0.3847 1.0000
8.250 1.3156 0.03464 0.02446 -0.0767 0.3751 1.0000
8.500 1.3397 0.03519 0.02518 -0.0760 0.3679 1.0000
8.750 1.3537 0.03652 0.02697 -0.0745 0.3595 1.0000
9.000 1.3761 0.03727 0.02797 -0.0737 0.3523 1.0000
9.250 1.3896 0.03862 0.02972 -0.0721 0.3437 1.0000
9.500 1.4036 0.03922 0.03057 -0.0702 0.3298 1.0000
9.750 1.4114 0.03905 0.03046 -0.0670 0.3069 1.0000
10.000 1.4100 0.03992 0.03156 -0.0636 0.2867 1.0000
10.250 1.4045 0.04079 0.03251 -0.0598 0.2648 1.0000
10.500 1.3897 0.04276 0.03469 -0.0561 0.2428 1.0000
10.750 1.3761 0.04519 0.03724 -0.0536 0.2163 1.0000
11.000 1.3653 0.04811 0.04022 -0.0522 0.1866 1.0000
11.250 1.3510 0.05173 0.04359 -0.0515 0.1534 1.0000
11.500 1.3338 0.05633 0.04797 -0.0515 0.1317 1.0000
11.750 1.3157 0.06159 0.05314 -0.0522 0.1155 1.0000
12.250 1.2834 0.07285 0.06454 -0.0547 0.0784 1.0000
12.500 1.2663 0.07891 0.07055 -0.0564 0.0692 1.0000
12.750 1.2496 0.08508 0.07665 -0.0583 0.0634 1.0000
13.000 1.2352 0.09104 0.08259 -0.0602 0.0584 1.0000
13.250 1.2223 0.09687 0.08840 -0.0620 0.0542 1.0000
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Polar data table (+)
Polar graphs
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