GOE 683 AIRFOIL (goe683-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: GOE 683 AIRFOIL (goe683-il) Reynolds number: 50,000 Max Cl/Cd: 21.07 at α=2.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe683-il-50000-n5.txt Download as CSV file: xf-goe683-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 683 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
------ -------- --------- --------- -------- -------- --------
-13.000 -0.3578 0.11318 0.10501 -0.0535 1.0000 0.1121
-12.750 -0.3800 0.10582 0.09769 -0.0565 1.0000 0.1129
-12.500 -0.3962 0.09976 0.09170 -0.0587 1.0000 0.1144
-12.250 -0.3914 0.09776 0.08975 -0.0583 1.0000 0.1161
-12.000 -0.4093 0.09173 0.08378 -0.0603 1.0000 0.1176
-11.750 -0.5867 0.06578 0.05754 -0.0725 1.0000 0.1163
-11.500 -0.6385 0.06107 0.05272 -0.0696 1.0000 0.1164
-11.250 -0.6774 0.05849 0.05008 -0.0646 1.0000 0.1166
-11.000 -0.7173 0.05697 0.04851 -0.0578 1.0000 0.1167
-10.750 -0.7496 0.05578 0.04725 -0.0515 0.9982 0.1171
-10.500 -0.7394 0.05326 0.04452 -0.0524 0.9832 0.1194
-10.250 -0.7349 0.05073 0.04167 -0.0519 0.9681 0.1217
-10.000 -0.7329 0.04821 0.03871 -0.0506 0.9532 0.1245
-9.750 -0.7078 0.04682 0.03730 -0.0516 0.9418 0.1275
-9.500 -0.6785 0.04528 0.03565 -0.0533 0.9327 0.1313
-9.250 -0.6622 0.04355 0.03362 -0.0528 0.9201 0.1352
-9.000 -0.6354 0.04191 0.03179 -0.0538 0.9109 0.1396
-8.750 -0.6056 0.04076 0.03060 -0.0550 0.9010 0.1445
-8.500 -0.5791 0.03921 0.02872 -0.0557 0.8915 0.1507
-8.250 -0.5484 0.03818 0.02772 -0.0568 0.8817 0.1565
-8.000 -0.5222 0.03710 0.02646 -0.0571 0.8717 0.1642
-7.750 -0.4931 0.03611 0.02545 -0.0577 0.8617 0.1720
-7.500 -0.4698 0.03523 0.02438 -0.0573 0.8511 0.1819
-7.250 -0.4424 0.03447 0.02367 -0.0574 0.8412 0.1922
-7.000 -0.4227 0.03384 0.02295 -0.0562 0.8301 0.2035
-6.750 -0.3983 0.03317 0.02211 -0.0557 0.8206 0.2175
-6.500 -0.3818 0.03284 0.02186 -0.0538 0.8092 0.2284
-6.250 -0.3563 0.03228 0.02122 -0.0533 0.8002 0.2422
-6.000 -0.3419 0.03203 0.02083 -0.0510 0.7889 0.2546
-5.750 -0.3149 0.03156 0.02035 -0.0508 0.7805 0.2685
-5.500 -0.2969 0.03133 0.02009 -0.0492 0.7699 0.2804
-5.250 -0.2723 0.03094 0.01962 -0.0485 0.7613 0.2963
-5.000 -0.2564 0.03079 0.01944 -0.0464 0.7513 0.3120
-4.750 -0.2323 0.03046 0.01914 -0.0457 0.7427 0.3295
-4.500 -0.2082 0.03017 0.01887 -0.0450 0.7340 0.3471
-4.250 -0.1847 0.02989 0.01864 -0.0443 0.7246 0.3649
-4.000 -0.1506 0.02938 0.01813 -0.0452 0.7180 0.3855
-3.750 -0.1317 0.02931 0.01813 -0.0438 0.7074 0.4025
-3.500 -0.0973 0.02881 0.01765 -0.0447 0.7007 0.4258
-3.250 -0.0788 0.02874 0.01768 -0.0432 0.6909 0.4492
-3.000 -0.0506 0.02839 0.01743 -0.0430 0.6834 0.4804
-2.750 -0.0237 0.02811 0.01728 -0.0427 0.6760 0.5177
-2.500 0.0019 0.02801 0.01742 -0.0421 0.6670 0.5609
-2.250 0.0575 0.02757 0.01720 -0.0463 0.6609 0.6253
-2.000 0.1109 0.02794 0.01778 -0.0504 0.6513 0.6860
-1.750 0.1793 0.02845 0.01830 -0.0562 0.6436 0.7370
-1.500 0.2294 0.02911 0.01887 -0.0590 0.6362 0.7740
-1.250 0.2626 0.02987 0.01957 -0.0592 0.6273 0.8063
-1.000 0.3039 0.03029 0.01980 -0.0606 0.6212 0.8354
-0.750 0.3327 0.03110 0.02055 -0.0606 0.6126 0.8622
-0.500 0.3705 0.03159 0.02091 -0.0621 0.6051 0.8858
-0.250 0.4111 0.03181 0.02092 -0.0639 0.5999 0.9081
0.000 0.4422 0.03261 0.02172 -0.0652 0.5903 0.9277
0.250 0.4899 0.03275 0.02172 -0.0689 0.5837 0.9451
0.500 0.5393 0.03290 0.02174 -0.0732 0.5771 0.9634
0.750 0.5864 0.03311 0.02192 -0.0778 0.5685 0.9813
1.000 0.6436 0.03257 0.02123 -0.0837 0.5627 0.9952
1.250 0.6664 0.03281 0.02143 -0.0840 0.5560 1.0000
1.500 0.6734 0.03332 0.02194 -0.0813 0.5492 1.0000
1.750 0.6897 0.03345 0.02196 -0.0797 0.5443 1.0000
2.000 0.7034 0.03376 0.02219 -0.0777 0.5393 1.0000
2.250 0.7033 0.03475 0.02325 -0.0740 0.5320 1.0000
2.500 0.7171 0.03509 0.02353 -0.0720 0.5269 1.0000
2.750 0.7393 0.03509 0.02341 -0.0710 0.5231 1.0000
3.000 0.7316 0.03653 0.02493 -0.0664 0.5157 1.0000
3.250 0.7382 0.03729 0.02569 -0.0635 0.5101 1.0000
3.500 0.7577 0.03747 0.02579 -0.0621 0.5061 1.0000
3.750 0.7663 0.03820 0.02650 -0.0595 0.5012 1.0000
4.000 0.7474 0.04020 0.02859 -0.0535 0.4937 1.0000
4.250 0.7607 0.04070 0.02906 -0.0514 0.4893 1.0000
4.500 0.7871 0.04064 0.02891 -0.0509 0.4861 1.0000
4.750 0.7352 0.04421 0.03261 -0.0413 0.4773 1.0000
5.000 0.7304 0.04549 0.03388 -0.0371 0.4718 1.0000
5.250 0.7562 0.04550 0.03383 -0.0365 0.4687 1.0000
5.500 0.7911 0.04517 0.03343 -0.0369 0.4663 1.0000
6.000 0.6884 0.05279 0.04114 -0.0206 0.4494 1.0000
7.500 0.6144 0.07147 0.05985 -0.0067 0.4092 1.0000
8.000 0.5906 0.07850 0.06691 -0.0038 0.3959 1.0000
8.250 0.6085 0.07930 0.06771 -0.0029 0.3937 1.0000
8.750 0.5786 0.08732 0.07578 -0.0009 0.3804 1.0000
9.000 0.5939 0.08841 0.07687 0.0000 0.3774 1.0000
9.250 0.6132 0.08914 0.07761 0.0009 0.3752 1.0000
9.500 0.5814 0.09517 0.08369 0.0013 0.3680 1.0000
9.750 0.5840 0.09758 0.08613 0.0020 0.3632 1.0000
10.000 0.5981 0.09884 0.08742 0.0027 0.3599 1.0000
10.250 0.6188 0.09948 0.08808 0.0036 0.3575 1.0000
10.500 0.5928 0.10494 0.09359 0.0036 0.3503 1.0000
10.750 0.5998 0.10681 0.09549 0.0043 0.3449 1.0000
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Polar data table (+)
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