GOE 369 AIRFOIL (goe369-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 369 AIRFOIL (goe369-il) Reynolds number: 200,000 Max Cl/Cd: 82.96 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe369-il-200000-n5.txt Download as CSV file: xf-goe369-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 369 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.2770 0.09584 0.09254 -0.0208 1.0000 0.0131
-7.500 -0.2747 0.09353 0.09028 -0.0206 1.0000 0.0131
-7.250 -0.2755 0.09291 0.08976 -0.0221 1.0000 0.0134
-7.000 -0.2700 0.09085 0.08776 -0.0239 1.0000 0.0135
-6.750 -0.2480 0.08752 0.08444 -0.0301 0.9892 0.0136
-6.500 -0.2167 0.08347 0.08036 -0.0382 0.9732 0.0136
-6.250 -0.1838 0.07926 0.07610 -0.0456 0.9527 0.0137
-6.000 -0.1487 0.07491 0.07167 -0.0529 0.9273 0.0137
-5.750 -0.1208 0.06882 0.06553 -0.0584 0.9016 0.0140
-5.500 -0.0967 0.06401 0.06064 -0.0612 0.8754 0.0144
-5.250 -0.0705 0.06031 0.05681 -0.0650 0.8486 0.0149
-5.000 -0.0461 0.05716 0.05351 -0.0684 0.8257 0.0154
-4.750 -0.0225 0.05426 0.05046 -0.0712 0.8071 0.0159
-4.500 0.0019 0.05144 0.04750 -0.0739 0.7916 0.0165
-4.250 0.0277 0.04864 0.04455 -0.0765 0.7784 0.0173
-4.000 0.0546 0.04592 0.04169 -0.0789 0.7664 0.0181
-3.750 0.0863 0.04344 0.03902 -0.0816 0.7554 0.0201
-3.500 0.1264 0.04177 0.03704 -0.0845 0.7459 0.0211
-3.250 0.1571 0.03954 0.03457 -0.0858 0.7370 0.0213
-3.000 0.1850 0.03706 0.03187 -0.0867 0.7287 0.0213
-2.750 0.2125 0.03466 0.02924 -0.0873 0.7209 0.0214
-2.500 0.2359 0.03075 0.02521 -0.0883 0.7135 0.0219
-2.250 0.2613 0.02840 0.02269 -0.0887 0.7066 0.0224
-2.000 0.2894 0.02635 0.02041 -0.0889 0.6996 0.0226
-1.750 0.3172 0.02456 0.01839 -0.0888 0.6928 0.0200
-1.500 0.3449 0.02249 0.01607 -0.0888 0.6861 0.0179
-1.250 0.3737 0.02090 0.01416 -0.0884 0.6780 0.0189
-1.000 0.4022 0.01937 0.01231 -0.0878 0.6690 0.0194
-0.750 0.4302 0.01787 0.01045 -0.0871 0.6606 0.0189
-0.500 0.4584 0.01652 0.00879 -0.0865 0.6525 0.0190
-0.250 0.4864 0.01548 0.00742 -0.0858 0.6464 0.0201
0.000 0.5138 0.01460 0.00632 -0.0853 0.6398 0.0226
0.250 0.5407 0.01386 0.00545 -0.0849 0.6335 0.0241
0.500 0.5675 0.01337 0.00486 -0.0844 0.6273 0.0277
0.750 0.5941 0.01296 0.00435 -0.0838 0.6202 0.0307
1.000 0.6199 0.01247 0.00387 -0.0833 0.6132 0.0350
1.250 0.6461 0.01226 0.00360 -0.0828 0.6046 0.0397
1.500 0.6722 0.01206 0.00334 -0.0824 0.5956 0.0447
1.750 0.6984 0.01201 0.00321 -0.0819 0.5866 0.0530
2.000 0.7248 0.01195 0.00318 -0.0814 0.5770 0.0729
2.250 0.7611 0.01030 0.00322 -0.0835 0.5668 1.0000
2.500 0.7871 0.01042 0.00322 -0.0830 0.5570 1.0000
2.750 0.8132 0.01054 0.00326 -0.0825 0.5453 1.0000
3.000 0.8387 0.01066 0.00330 -0.0820 0.5305 1.0000
3.250 0.8640 0.01081 0.00335 -0.0813 0.5127 1.0000
3.500 0.8893 0.01096 0.00343 -0.0808 0.4956 1.0000
3.750 0.9144 0.01114 0.00353 -0.0802 0.4750 1.0000
4.000 0.9389 0.01136 0.00366 -0.0795 0.4520 1.0000
4.250 0.9632 0.01161 0.00381 -0.0788 0.4268 1.0000
4.500 0.9870 0.01193 0.00400 -0.0781 0.3989 1.0000
4.750 1.0100 0.01232 0.00426 -0.0773 0.3694 1.0000
5.000 1.0327 0.01276 0.00456 -0.0765 0.3414 1.0000
5.250 1.0555 0.01321 0.00490 -0.0757 0.3170 1.0000
5.500 1.0783 0.01367 0.00527 -0.0749 0.2931 1.0000
5.750 1.1009 0.01414 0.00570 -0.0742 0.2674 1.0000
6.000 1.1229 0.01468 0.00613 -0.0734 0.2388 1.0000
6.250 1.1442 0.01527 0.00661 -0.0725 0.2112 1.0000
6.500 1.1649 0.01593 0.00718 -0.0716 0.1894 1.0000
6.750 1.1858 0.01655 0.00775 -0.0707 0.1736 1.0000
7.000 1.2064 0.01720 0.00836 -0.0697 0.1610 1.0000
7.250 1.2275 0.01777 0.00896 -0.0688 0.1495 1.0000
7.500 1.2485 0.01833 0.00959 -0.0679 0.1392 1.0000
7.750 1.2687 0.01896 0.01023 -0.0669 0.1305 1.0000
8.000 1.2893 0.01952 0.01086 -0.0660 0.1224 1.0000
8.250 1.3089 0.02016 0.01155 -0.0649 0.1162 1.0000
8.500 1.3286 0.02076 0.01225 -0.0639 0.1105 1.0000
8.750 1.3464 0.02150 0.01306 -0.0626 0.1056 1.0000
9.000 1.3649 0.02217 0.01386 -0.0614 0.1017 1.0000
9.250 1.3826 0.02287 0.01467 -0.0601 0.0971 1.0000
9.500 1.3980 0.02368 0.01550 -0.0587 0.0905 1.0000
9.750 1.4152 0.02432 0.01622 -0.0575 0.0817 1.0000
10.000 1.4309 0.02506 0.01704 -0.0561 0.0743 1.0000
10.250 1.4439 0.02587 0.01791 -0.0544 0.0648 1.0000
10.500 1.4574 0.02662 0.01873 -0.0526 0.0540 1.0000
10.750 1.4634 0.02790 0.01990 -0.0502 0.0362 1.0000
11.000 1.4559 0.03032 0.02209 -0.0467 0.0138 1.0000
11.250 1.4542 0.03244 0.02429 -0.0441 0.0104 1.0000
11.500 1.4565 0.03434 0.02638 -0.0422 0.0092 1.0000
11.750 1.4577 0.03646 0.02870 -0.0407 0.0084 1.0000
12.000 1.4570 0.03889 0.03134 -0.0394 0.0079 1.0000
12.250 1.4512 0.04203 0.03468 -0.0384 0.0072 1.0000
12.500 1.4484 0.04498 0.03784 -0.0378 0.0067 1.0000
12.750 1.4456 0.04806 0.04112 -0.0375 0.0064 1.0000
13.000 1.4405 0.05155 0.04482 -0.0376 0.0060 1.0000
13.250 1.4340 0.05537 0.04883 -0.0380 0.0058 1.0000
13.500 1.4252 0.05965 0.05331 -0.0387 0.0057 1.0000
13.750 1.4148 0.06435 0.05819 -0.0398 0.0055 1.0000
14.000 1.4030 0.06946 0.06350 -0.0413 0.0054 1.0000
14.250 1.3907 0.07490 0.06912 -0.0432 0.0054 1.0000
14.500 1.3752 0.08121 0.07561 -0.0457 0.0053 1.0000
14.750 1.3613 0.08762 0.08219 -0.0485 0.0053 1.0000
15.000 1.3455 0.09472 0.08948 -0.0518 0.0053 1.0000
15.250 1.3306 0.10202 0.09695 -0.0554 0.0053 1.0000
15.500 1.3149 0.10973 0.10484 -0.0593 0.0053 1.0000
15.750 1.2994 0.11764 0.11291 -0.0633 0.0053 1.0000
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Polar data table (+)
Polar graphs
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