GOE 599 AIRFOIL (goe599-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 599 AIRFOIL (goe599-il) Reynolds number: 100,000 Max Cl/Cd: 48.51 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe599-il-100000.txt Download as CSV file: xf-goe599-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 599 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.5330 0.09315 0.08813 -0.0244 1.0000 0.1428
-8.750 -0.5368 0.08953 0.08456 -0.0258 1.0000 0.1484
-8.500 -0.5948 0.08374 0.07894 -0.0363 1.0000 0.1518
-8.250 -0.5549 0.08149 0.07668 -0.0283 1.0000 0.1565
-8.000 -0.6100 0.07640 0.07157 -0.0372 1.0000 0.1660
-7.750 -0.6448 0.05400 0.04817 -0.0437 1.0000 0.0805
-7.500 -0.6262 0.05451 0.04909 -0.0421 1.0000 0.0994
-7.250 -0.6428 0.04317 0.03602 -0.0399 1.0000 0.0694
-7.000 -0.6300 0.03888 0.03149 -0.0386 1.0000 0.0682
-6.750 -0.6159 0.03531 0.02753 -0.0370 1.0000 0.0676
-6.500 -0.5993 0.03229 0.02403 -0.0354 1.0000 0.0678
-6.250 -0.5811 0.02977 0.02103 -0.0339 1.0000 0.0701
-6.000 -0.5610 0.02779 0.01897 -0.0329 1.0000 0.0735
-5.750 -0.5391 0.02597 0.01689 -0.0317 1.0000 0.0762
-5.500 -0.5165 0.02460 0.01517 -0.0304 1.0000 0.0809
-5.250 -0.4944 0.02305 0.01366 -0.0296 1.0000 0.0870
-5.000 -0.4710 0.02193 0.01235 -0.0285 1.0000 0.0937
-4.750 -0.4486 0.02067 0.01116 -0.0277 1.0000 0.1043
-4.500 -0.4258 0.01939 0.00995 -0.0268 1.0000 0.1171
-4.250 -0.4036 0.01805 0.00882 -0.0260 1.0000 0.1435
-4.000 -0.3806 0.01636 0.00791 -0.0256 1.0000 0.2514
-3.750 -0.3582 0.01545 0.00762 -0.0251 1.0000 0.3771
-3.500 -0.3359 0.01501 0.00750 -0.0243 1.0000 0.4659
-3.250 -0.3144 0.01476 0.00755 -0.0230 1.0000 0.5518
-3.000 -0.2938 0.01456 0.00762 -0.0214 1.0000 0.6298
-2.750 -0.2743 0.01441 0.00766 -0.0193 1.0000 0.6978
-2.500 -0.2555 0.01431 0.00772 -0.0169 1.0000 0.7580
-2.250 -0.2384 0.01427 0.00781 -0.0140 1.0000 0.8205
-2.000 -0.2195 0.01430 0.00794 -0.0113 1.0000 0.8927
-1.750 -0.1692 0.01445 0.00797 -0.0158 1.0000 0.9812
-1.500 -0.1450 0.01445 0.00777 -0.0168 1.0000 1.0000
-1.250 -0.1258 0.01458 0.00771 -0.0165 1.0000 1.0000
-1.000 -0.1052 0.01478 0.00776 -0.0162 1.0000 1.0000
-0.750 -0.0840 0.01503 0.00786 -0.0160 1.0000 1.0000
-0.500 -0.0625 0.01532 0.00804 -0.0158 1.0000 1.0000
-0.250 -0.0410 0.01566 0.00827 -0.0157 1.0000 1.0000
0.000 0.0024 0.01612 0.00863 -0.0197 0.9941 1.0000
0.250 0.0537 0.01655 0.00898 -0.0251 0.9842 1.0000
0.500 0.1008 0.01687 0.00925 -0.0296 0.9734 1.0000
0.750 0.1452 0.01714 0.00950 -0.0335 0.9626 1.0000
1.000 0.1906 0.01738 0.00974 -0.0374 0.9528 1.0000
1.250 0.2368 0.01755 0.00993 -0.0414 0.9431 1.0000
1.500 0.2760 0.01766 0.01007 -0.0439 0.9311 1.0000
1.750 0.3163 0.01772 0.01020 -0.0465 0.9194 1.0000
2.000 0.3602 0.01765 0.01022 -0.0496 0.9075 1.0000
2.250 0.4124 0.01716 0.00984 -0.0535 0.8925 1.0000
2.500 0.4637 0.01633 0.00915 -0.0565 0.8754 1.0000
2.750 0.5102 0.01549 0.00843 -0.0584 0.8577 1.0000
3.000 0.5450 0.01492 0.00794 -0.0581 0.8347 1.0000
3.250 0.5786 0.01437 0.00747 -0.0575 0.8073 1.0000
3.500 0.6063 0.01411 0.00724 -0.0561 0.7767 1.0000
3.750 0.6314 0.01392 0.00704 -0.0542 0.7387 1.0000
4.000 0.6540 0.01387 0.00700 -0.0521 0.6945 1.0000
4.250 0.6748 0.01391 0.00692 -0.0495 0.6309 1.0000
4.500 0.6897 0.01445 0.00682 -0.0457 0.4972 1.0000
4.750 0.6889 0.01690 0.00744 -0.0405 0.2034 1.0000
5.000 0.7028 0.01859 0.00859 -0.0383 0.1563 1.0000
5.250 0.7216 0.01969 0.00963 -0.0366 0.1423 1.0000
5.500 0.7422 0.02071 0.01065 -0.0352 0.1334 1.0000
5.750 0.7633 0.02195 0.01174 -0.0341 0.1251 1.0000
6.000 0.7880 0.02294 0.01281 -0.0333 0.1187 1.0000
6.250 0.8141 0.02439 0.01414 -0.0330 0.1129 1.0000
6.500 0.8401 0.02564 0.01554 -0.0324 0.1063 1.0000
6.750 0.8665 0.02727 0.01710 -0.0323 0.0994 1.0000
7.000 0.8918 0.02888 0.01899 -0.0315 0.0929 1.0000
7.250 0.9175 0.03133 0.02136 -0.0316 0.0855 1.0000
7.500 0.9391 0.03324 0.02381 -0.0299 0.0811 1.0000
7.750 0.9610 0.03527 0.02598 -0.0290 0.0751 1.0000
8.000 0.9803 0.03955 0.03048 -0.0281 0.0721 1.0000
8.250 0.9946 0.04237 0.03391 -0.0256 0.0709 1.0000
8.500 1.0049 0.04544 0.03759 -0.0228 0.0690 1.0000
8.750 1.0125 0.04915 0.04180 -0.0202 0.0682 1.0000
9.000 1.0183 0.05375 0.04681 -0.0178 0.0697 1.0000
9.250 1.0065 0.06041 0.05432 -0.0134 0.0805 1.0000
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Polar data table (+)
Polar graphs
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