GOE 397 AIRFOIL (goe397-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 397 AIRFOIL (goe397-il) Reynolds number: 200,000 Max Cl/Cd: 81.7 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe397-il-200000.txt Download as CSV file: xf-goe397-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 397 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.250 -0.3806 0.08734 0.08396 -0.0301 1.0000 0.0280
-7.000 -0.3769 0.08280 0.07945 -0.0278 1.0000 0.0286
-6.750 -0.3702 0.07938 0.07606 -0.0268 1.0000 0.0292
-6.500 -0.3628 0.07633 0.07303 -0.0270 1.0000 0.0300
-6.250 -0.3543 0.07331 0.07001 -0.0282 1.0000 0.0310
-6.000 -0.3447 0.07033 0.06705 -0.0297 1.0000 0.0325
-5.750 -0.3339 0.06734 0.06406 -0.0315 1.0000 0.0339
-5.500 -0.3197 0.06444 0.06115 -0.0343 1.0000 0.0365
-5.250 -0.2924 0.06244 0.05898 -0.0404 1.0000 0.0384
-5.000 -0.2828 0.06024 0.05671 -0.0404 1.0000 0.0386
-4.750 -0.2694 0.05756 0.05390 -0.0410 0.9993 0.0387
-4.500 -0.2508 0.05009 0.04652 -0.0446 0.9946 0.0408
-4.250 -0.2177 0.04659 0.04296 -0.0487 0.9888 0.0438
-4.000 -0.1527 0.04427 0.03997 -0.0574 0.9835 0.0520
-3.750 -0.1323 0.03823 0.03409 -0.0603 0.9768 0.0553
-3.250 -0.0536 0.03187 0.02726 -0.0682 0.9651 0.0696
-3.000 -0.0137 0.02929 0.02439 -0.0716 0.9590 0.0823
-2.750 0.0272 0.02702 0.02184 -0.0751 0.9550 0.0958
-2.500 0.0608 0.02518 0.01979 -0.0768 0.9459 0.1095
-2.250 0.0968 0.02326 0.01773 -0.0791 0.9398 0.1242
-2.000 0.1283 0.02176 0.01617 -0.0803 0.9303 0.1427
-1.500 0.2042 0.01637 0.00945 -0.0805 0.9137 0.0735
-1.250 0.2348 0.01516 0.00779 -0.0800 0.9023 0.0665
-1.000 0.2630 0.01416 0.00664 -0.0797 0.8900 0.0672
-0.750 0.2898 0.01338 0.00578 -0.0790 0.8762 0.0685
-0.500 0.3160 0.01282 0.00510 -0.0780 0.8620 0.0673
-0.250 0.3418 0.01233 0.00454 -0.0771 0.8494 0.0672
0.000 0.3674 0.01188 0.00408 -0.0764 0.8387 0.0681
0.250 0.3932 0.01155 0.00375 -0.0756 0.8289 0.0703
0.500 0.4185 0.01135 0.00356 -0.0750 0.8180 0.0743
0.750 0.4443 0.01120 0.00340 -0.0743 0.8083 0.0811
1.000 0.4703 0.01103 0.00330 -0.0737 0.7996 0.1064
1.250 0.5203 0.00896 0.00321 -0.0787 0.7908 1.0000
1.500 0.5459 0.00909 0.00324 -0.0781 0.7814 1.0000
1.750 0.5717 0.00922 0.00329 -0.0774 0.7727 1.0000
2.000 0.5971 0.00934 0.00340 -0.0768 0.7626 1.0000
2.250 0.6227 0.00947 0.00349 -0.0762 0.7530 1.0000
2.500 0.6485 0.00959 0.00357 -0.0755 0.7442 1.0000
2.750 0.6737 0.00970 0.00369 -0.0748 0.7325 1.0000
3.000 0.6984 0.00975 0.00373 -0.0738 0.7173 1.0000
3.250 0.7226 0.00980 0.00376 -0.0726 0.6993 1.0000
3.500 0.7469 0.00987 0.00382 -0.0716 0.6804 1.0000
3.750 0.7705 0.00994 0.00384 -0.0702 0.6560 1.0000
4.000 0.7939 0.01006 0.00394 -0.0690 0.6291 1.0000
4.250 0.8177 0.01023 0.00408 -0.0678 0.6034 1.0000
4.500 0.8412 0.01037 0.00425 -0.0667 0.5710 1.0000
4.750 0.8627 0.01056 0.00435 -0.0651 0.5088 1.0000
5.000 0.8759 0.01159 0.00463 -0.0623 0.3705 1.0000
5.250 0.8793 0.01441 0.00593 -0.0591 0.1116 1.0000
5.500 0.8975 0.01559 0.00694 -0.0576 0.0806 1.0000
5.750 0.9148 0.01687 0.00819 -0.0559 0.0643 1.0000
6.000 0.9317 0.01823 0.00953 -0.0541 0.0517 1.0000
6.250 0.9517 0.01929 0.01066 -0.0526 0.0447 1.0000
6.500 0.9680 0.02155 0.01287 -0.0508 0.0400 1.0000
6.750 0.9909 0.02235 0.01385 -0.0497 0.0361 1.0000
7.000 1.0128 0.02371 0.01529 -0.0486 0.0330 1.0000
7.250 1.0351 0.02561 0.01725 -0.0477 0.0311 1.0000
7.500 1.0585 0.02896 0.02077 -0.0469 0.0299 1.0000
7.750 1.0789 0.03336 0.02553 -0.0457 0.0292 1.0000
8.000 1.0982 0.03403 0.02658 -0.0439 0.0277 1.0000
8.250 1.1148 0.03725 0.03021 -0.0421 0.0274 1.0000
8.500 1.1267 0.04154 0.03496 -0.0400 0.0279 1.0000
8.750 1.1423 0.04610 0.03973 -0.0387 0.0301 1.0000
10.750 0.9865 0.08617 0.08251 -0.0181 0.0524 1.0000
11.000 0.9619 0.09112 0.08758 -0.0189 0.0524 1.0000
11.250 0.9368 0.09675 0.09327 -0.0208 0.0524 1.0000
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Polar data table (+)
Polar graphs
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