GOE 518 AIRFOIL (goe518-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 518 AIRFOIL (goe518-il) Reynolds number: 50,000 Max Cl/Cd: 23.75 at α=3.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe518-il-50000-n5.txt Download as CSV file: xf-goe518-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 518 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
------ -------- --------- --------- -------- -------- --------
-8.000 -0.0555 0.10799 0.10178 -0.0746 0.8832 0.1475
-7.750 -0.0587 0.10550 0.09932 -0.0762 0.8734 0.1523
-7.500 -0.1009 0.10455 0.09841 -0.0782 0.8598 0.1555
-7.250 -0.1049 0.10129 0.09520 -0.0776 0.8477 0.1570
-7.000 -0.0562 0.09638 0.09027 -0.0784 0.8446 0.1620
-6.750 -0.0655 0.09435 0.08827 -0.0761 0.8309 0.1642
-6.500 -0.0722 0.09188 0.08580 -0.0753 0.8186 0.1669
-6.000 -0.1140 0.07723 0.07037 -0.0813 0.7944 0.0853
-5.750 -0.1054 0.07486 0.06801 -0.0795 0.7837 0.0842
-5.500 -0.0914 0.07153 0.06457 -0.0794 0.7756 0.0827
-5.250 -0.0909 0.06905 0.06195 -0.0771 0.7633 0.0818
-5.000 -0.0746 0.06534 0.05799 -0.0773 0.7565 0.0815
-4.750 -0.0734 0.06321 0.05567 -0.0745 0.7435 0.0813
-4.500 -0.0517 0.05965 0.05178 -0.0746 0.7379 0.0810
-4.250 -0.0487 0.05774 0.04965 -0.0716 0.7246 0.0804
-4.000 -0.0234 0.05422 0.04570 -0.0714 0.7196 0.0792
-3.750 -0.0181 0.05256 0.04374 -0.0683 0.7064 0.0785
-3.500 0.0031 0.05000 0.04076 -0.0670 0.6988 0.0779
-3.250 0.0196 0.04816 0.03858 -0.0650 0.6886 0.0778
-3.000 0.0429 0.04637 0.03649 -0.0639 0.6803 0.0786
-2.750 0.0648 0.04488 0.03474 -0.0625 0.6707 0.0800
-2.500 0.0911 0.04324 0.03276 -0.0617 0.6625 0.0815
-2.250 0.1156 0.04184 0.03102 -0.0605 0.6529 0.0822
-2.000 0.1508 0.04000 0.02879 -0.0607 0.6464 0.0830
-1.750 0.1726 0.03912 0.02764 -0.0592 0.6350 0.0837
-1.500 0.2166 0.03731 0.02540 -0.0606 0.6292 0.0854
-1.250 0.2353 0.03695 0.02499 -0.0590 0.6164 0.0871
-1.000 0.2775 0.03568 0.02353 -0.0606 0.6091 0.0913
-0.750 0.3040 0.03533 0.02297 -0.0600 0.5972 0.0944
-0.500 0.3509 0.03437 0.02179 -0.0627 0.5884 0.0980
-0.250 0.3801 0.03405 0.02135 -0.0627 0.5773 0.1024
0.000 0.4114 0.03367 0.02077 -0.0629 0.5676 0.1093
0.250 0.4386 0.03336 0.02039 -0.0626 0.5577 0.1185
0.500 0.4647 0.03310 0.02004 -0.0621 0.5485 0.1302
0.750 0.4888 0.03286 0.01979 -0.0614 0.5393 0.1540
1.000 0.6496 0.03076 0.01976 -0.0865 0.5257 1.0000
1.250 0.6768 0.03092 0.01956 -0.0862 0.5181 1.0000
1.500 0.6879 0.03151 0.01998 -0.0836 0.5100 1.0000
1.750 0.7062 0.03195 0.02020 -0.0820 0.5028 1.0000
2.000 0.7368 0.03212 0.02005 -0.0823 0.4970 1.0000
2.250 0.7386 0.03301 0.02090 -0.0784 0.4893 1.0000
2.500 0.7612 0.03338 0.02106 -0.0776 0.4834 1.0000
2.750 0.7869 0.03372 0.02117 -0.0773 0.4781 1.0000
3.000 0.7875 0.03475 0.02218 -0.0733 0.4714 1.0000
3.250 0.8075 0.03526 0.02254 -0.0722 0.4662 1.0000
3.500 0.8412 0.03542 0.02246 -0.0731 0.4622 1.0000
3.750 0.8377 0.03674 0.02381 -0.0688 0.4568 1.0000
4.000 0.8427 0.03785 0.02491 -0.0659 0.4518 1.0000
4.250 0.8629 0.03844 0.02537 -0.0649 0.4477 1.0000
4.500 0.8954 0.03864 0.02537 -0.0656 0.4444 1.0000
4.750 0.8821 0.04052 0.02734 -0.0605 0.4393 1.0000
5.000 0.8727 0.04244 0.02933 -0.0562 0.4341 1.0000
5.250 0.8856 0.04344 0.03026 -0.0546 0.4303 1.0000
5.500 0.9119 0.04385 0.03054 -0.0545 0.4275 1.0000
5.750 0.9409 0.04422 0.03078 -0.0548 0.4252 1.0000
6.000 0.8244 0.05329 0.04038 -0.0421 0.4157 1.0000
6.250 0.8245 0.05559 0.04267 -0.0402 0.4117 1.0000
6.500 0.8477 0.05605 0.04304 -0.0397 0.4094 1.0000
6.750 0.8804 0.05582 0.04269 -0.0398 0.4077 1.0000
7.250 0.7461 0.07493 0.06225 -0.0332 0.3899 1.0000
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Polar data table (+)
Polar graphs
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