GOE 391 AIRFOIL (goe391-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 391 AIRFOIL (goe391-il) Reynolds number: 500,000 Max Cl/Cd: 105.98 at α=1.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe391-il-500000.txt Download as CSV file: xf-goe391-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 391 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.4429 0.09065 0.08845 -0.0213 1.0000 0.0114
-7.500 -0.4438 0.08768 0.08551 -0.0220 1.0000 0.0114
-7.250 -0.4517 0.08293 0.08081 -0.0202 1.0000 0.0118
-7.000 -0.4521 0.08029 0.07818 -0.0195 1.0000 0.0120
-6.750 -0.4523 0.07781 0.07571 -0.0187 1.0000 0.0123
-6.500 -0.4515 0.07519 0.07311 -0.0187 1.0000 0.0125
-6.250 -0.4490 0.07246 0.07038 -0.0189 1.0000 0.0128
-6.000 -0.4449 0.06972 0.06763 -0.0192 1.0000 0.0133
-5.750 -0.4202 0.06551 0.06336 -0.0245 0.9982 0.0147
-5.500 -0.3735 0.06092 0.05862 -0.0339 0.9956 0.0166
-5.250 -0.3387 0.05669 0.05426 -0.0393 0.9934 0.0168
-5.000 -0.3081 0.05244 0.04986 -0.0431 0.9903 0.0169
-4.750 -0.2753 0.04804 0.04529 -0.0470 0.9874 0.0170
-4.500 -0.2405 0.04361 0.04067 -0.0508 0.9851 0.0170
-4.250 -0.2126 0.03619 0.03304 -0.0555 0.9830 0.0180
-4.000 -0.1872 0.03352 0.03025 -0.0566 0.9781 0.0186
-3.750 -0.1557 0.03085 0.02742 -0.0586 0.9749 0.0200
-3.500 -0.1152 0.02971 0.02602 -0.0598 0.9729 0.0249
-2.250 0.0393 0.01471 0.00929 -0.0632 0.9595 0.0278
-2.000 0.0758 0.01415 0.00870 -0.0653 0.9580 0.0326
-1.750 0.1122 0.01236 0.00665 -0.0666 0.9569 0.0326
-1.500 0.1446 0.01146 0.00561 -0.0673 0.9543 0.0344
-1.250 0.1736 0.01102 0.00509 -0.0673 0.9495 0.0376
-1.000 0.2061 0.00990 0.00393 -0.0682 0.9467 0.0392
-0.750 0.2412 0.00924 0.00327 -0.0697 0.9438 0.0413
-0.500 0.2694 0.00884 0.00288 -0.0696 0.9378 0.0439
-0.250 0.2993 0.00844 0.00248 -0.0699 0.9324 0.0459
0.000 0.3294 0.00812 0.00214 -0.0701 0.9258 0.0482
0.250 0.3579 0.00789 0.00189 -0.0700 0.9177 0.0498
0.500 0.3849 0.00768 0.00168 -0.0696 0.9085 0.0531
1.000 0.4894 0.00516 0.00150 -0.0806 0.8796 1.0000
1.250 0.5149 0.00516 0.00142 -0.0798 0.8618 1.0000
1.500 0.5389 0.00520 0.00136 -0.0787 0.8343 1.0000
1.750 0.5617 0.00530 0.00131 -0.0773 0.7965 1.0000
2.000 0.5813 0.00554 0.00127 -0.0752 0.7297 1.0000
2.250 0.5974 0.00600 0.00132 -0.0725 0.6429 1.0000
2.750 0.6320 0.00703 0.00165 -0.0681 0.4835 1.0000
3.000 0.6469 0.00787 0.00190 -0.0657 0.3532 1.0000
3.250 0.6664 0.00843 0.00216 -0.0642 0.2870 1.0000
3.500 0.6835 0.00928 0.00248 -0.0623 0.1694 1.0000
3.750 0.7005 0.01022 0.00292 -0.0604 0.0651 1.0000
4.000 0.7227 0.01065 0.00327 -0.0593 0.0488 1.0000
4.250 0.7453 0.01105 0.00370 -0.0582 0.0434 1.0000
4.500 0.7675 0.01152 0.00423 -0.0570 0.0410 1.0000
4.750 0.7903 0.01189 0.00466 -0.0560 0.0399 1.0000
5.000 0.8128 0.01230 0.00513 -0.0550 0.0379 1.0000
5.250 0.8346 0.01282 0.00571 -0.0538 0.0356 1.0000
5.500 0.8550 0.01351 0.00646 -0.0525 0.0319 1.0000
5.750 0.8723 0.01473 0.00778 -0.0505 0.0285 1.0000
6.000 0.8954 0.01515 0.00827 -0.0496 0.0261 1.0000
6.250 0.9173 0.01576 0.00894 -0.0485 0.0231 1.0000
6.500 0.9362 0.01696 0.01015 -0.0471 0.0196 1.0000
6.750 0.9568 0.01822 0.01157 -0.0458 0.0181 1.0000
7.000 0.9792 0.01904 0.01250 -0.0447 0.0166 1.0000
7.250 1.0010 0.02006 0.01364 -0.0436 0.0152 1.0000
7.500 1.0224 0.02086 0.01453 -0.0425 0.0140 1.0000
7.750 1.0418 0.02217 0.01592 -0.0414 0.0128 1.0000
8.000 1.0578 0.02530 0.01942 -0.0395 0.0119 1.0000
8.250 1.0753 0.02733 0.02173 -0.0377 0.0115 1.0000
8.500 1.0894 0.03007 0.02487 -0.0354 0.0108 1.0000
8.750 1.0971 0.03390 0.02916 -0.0323 0.0106 1.0000
9.000 1.0974 0.03856 0.03430 -0.0285 0.0106 1.0000
9.250 1.0910 0.04368 0.03987 -0.0243 0.0108 1.0000
9.500 1.0799 0.04848 0.04503 -0.0203 0.0111 1.0000
9.750 1.0638 0.05303 0.04985 -0.0165 0.0115 1.0000
10.000 0.9853 0.04663 0.04377 -0.0077 0.0115 1.0000
10.250 0.9609 0.05061 0.04791 -0.0052 0.0116 1.0000
10.500 0.9355 0.05534 0.05279 -0.0044 0.0116 1.0000
10.750 0.9116 0.06071 0.05829 -0.0053 0.0117 1.0000
11.000 0.8873 0.06730 0.06498 -0.0082 0.0117 1.0000
11.250 0.8637 0.07524 0.07303 -0.0128 0.0117 1.0000
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Polar data table (+)
Polar graphs
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