GOE 758 AIRFOIL (goe758-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 758 AIRFOIL (goe758-il) Reynolds number: 200,000 Max Cl/Cd: 75.58 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe758-il-200000-n5.txt Download as CSV file: xf-goe758-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 758 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
------ -------- --------- --------- -------- -------- --------
-11.000 -0.2682 0.11207 0.10849 -0.0460 1.0000 0.0403
-10.750 -0.2868 0.10667 0.10316 -0.0507 1.0000 0.0420
-10.500 -0.2882 0.10227 0.09881 -0.0530 0.9937 0.0421
-10.000 -0.2531 0.09540 0.09192 -0.0569 0.9708 0.0434
-9.750 -0.2539 0.08546 0.08193 -0.0656 0.9556 0.0350
-9.500 -0.2347 0.08144 0.07787 -0.0702 0.9421 0.0344
-9.250 -0.2191 0.07569 0.07207 -0.0774 0.9276 0.0338
-9.000 -0.2080 0.06869 0.06501 -0.0862 0.9108 0.0333
-8.750 -0.2119 0.05942 0.05567 -0.0970 0.8892 0.0332
-8.500 -0.2516 0.04692 0.04280 -0.1084 0.8638 0.0327
-8.250 -0.2652 0.04137 0.03683 -0.1095 0.8466 0.0326
-8.000 -0.2667 0.03733 0.03235 -0.1092 0.8318 0.0327
-7.750 -0.2612 0.03409 0.02869 -0.1083 0.8177 0.0328
-7.500 -0.2506 0.03142 0.02562 -0.1073 0.8039 0.0329
-7.250 -0.2365 0.02919 0.02300 -0.1062 0.7899 0.0331
-7.000 -0.2196 0.02739 0.02080 -0.1052 0.7757 0.0336
-6.750 -0.2006 0.02592 0.01894 -0.1042 0.7614 0.0342
-6.500 -0.1801 0.02462 0.01728 -0.1033 0.7475 0.0347
-6.250 -0.1585 0.02343 0.01577 -0.1024 0.7336 0.0348
-6.000 -0.1359 0.02240 0.01443 -0.1016 0.7200 0.0350
-5.750 -0.1124 0.02152 0.01328 -0.1009 0.7076 0.0352
-5.500 -0.0883 0.02074 0.01226 -0.1002 0.6969 0.0354
-5.000 -0.0397 0.01885 0.01011 -0.0991 0.6787 0.0361
-4.750 -0.0150 0.01820 0.00936 -0.0987 0.6712 0.0369
-4.500 0.0101 0.01765 0.00875 -0.0982 0.6639 0.0377
-4.250 0.0354 0.01716 0.00816 -0.0977 0.6575 0.0383
-4.000 0.0607 0.01669 0.00760 -0.0972 0.6515 0.0387
-3.750 0.0861 0.01626 0.00711 -0.0968 0.6455 0.0391
-3.500 0.1115 0.01589 0.00665 -0.0963 0.6403 0.0396
-3.250 0.1370 0.01555 0.00625 -0.0958 0.6352 0.0401
-3.000 0.1625 0.01525 0.00590 -0.0954 0.6297 0.0406
-2.750 0.1883 0.01501 0.00557 -0.0950 0.6249 0.0412
-2.500 0.2143 0.01480 0.00529 -0.0946 0.6203 0.0419
-2.250 0.2401 0.01456 0.00502 -0.0942 0.6150 0.0429
-2.000 0.2661 0.01437 0.00476 -0.0939 0.6102 0.0450
-1.750 0.2927 0.01426 0.00456 -0.0936 0.6058 0.0470
-1.500 0.3190 0.01413 0.00441 -0.0933 0.6005 0.0489
-1.250 0.3453 0.01402 0.00427 -0.0929 0.5952 0.0518
-1.000 0.3718 0.01391 0.00415 -0.0926 0.5907 0.0602
-0.750 0.3967 0.01355 0.00407 -0.0922 0.5858 0.1347
-0.500 0.4202 0.01302 0.00406 -0.0917 0.5807 0.2841
-0.250 0.4441 0.01268 0.00409 -0.0912 0.5762 0.3969
0.000 0.4674 0.01241 0.00418 -0.0903 0.5720 0.5196
0.250 0.4910 0.01223 0.00427 -0.0894 0.5668 0.6008
0.500 0.5154 0.01212 0.00431 -0.0885 0.5620 0.6582
0.750 0.5389 0.01190 0.00434 -0.0873 0.5578 0.7453
1.000 0.6215 0.01158 0.00441 -0.0984 0.5510 0.9971
1.250 0.6483 0.01169 0.00444 -0.0983 0.5457 1.0000
1.500 0.6729 0.01181 0.00444 -0.0976 0.5412 1.0000
1.750 0.6971 0.01191 0.00452 -0.0969 0.5356 1.0000
2.000 0.7215 0.01202 0.00458 -0.0963 0.5300 1.0000
2.250 0.7462 0.01215 0.00461 -0.0956 0.5252 1.0000
2.500 0.7707 0.01226 0.00472 -0.0950 0.5191 1.0000
2.750 0.7952 0.01238 0.00480 -0.0944 0.5133 1.0000
3.000 0.8198 0.01252 0.00487 -0.0937 0.5081 1.0000
3.250 0.8441 0.01264 0.00501 -0.0931 0.5012 1.0000
3.500 0.8685 0.01278 0.00510 -0.0925 0.4953 1.0000
3.750 0.8929 0.01293 0.00523 -0.0918 0.4890 1.0000
4.000 0.9170 0.01308 0.00537 -0.0912 0.4822 1.0000
4.250 0.9410 0.01324 0.00550 -0.0905 0.4758 1.0000
4.500 0.9648 0.01341 0.00567 -0.0898 0.4685 1.0000
4.750 0.9885 0.01359 0.00581 -0.0890 0.4623 1.0000
5.000 1.0121 0.01378 0.00603 -0.0883 0.4547 1.0000
5.250 1.0352 0.01398 0.00619 -0.0875 0.4477 1.0000
5.500 1.0584 0.01419 0.00644 -0.0867 0.4400 1.0000
5.750 1.0811 0.01442 0.00665 -0.0859 0.4332 1.0000
6.000 1.1038 0.01466 0.00691 -0.0851 0.4259 1.0000
6.250 1.1255 0.01492 0.00715 -0.0841 0.4179 1.0000
6.500 1.1473 0.01518 0.00743 -0.0831 0.4096 1.0000
6.750 1.1682 0.01547 0.00770 -0.0820 0.4018 1.0000
7.000 1.1893 0.01576 0.00803 -0.0809 0.3937 1.0000
7.250 1.2095 0.01608 0.00835 -0.0797 0.3865 1.0000
7.500 1.2301 0.01639 0.00870 -0.0786 0.3795 1.0000
7.750 1.2495 0.01674 0.00906 -0.0773 0.3725 1.0000
8.000 1.2690 0.01709 0.00946 -0.0761 0.3660 1.0000
8.250 1.2875 0.01745 0.00986 -0.0747 0.3591 1.0000
8.500 1.3049 0.01786 0.01028 -0.0731 0.3524 1.0000
8.750 1.3193 0.01825 0.01071 -0.0710 0.3434 1.0000
9.000 1.3323 0.01869 0.01118 -0.0687 0.3349 1.0000
9.250 1.3437 0.01919 0.01168 -0.0662 0.3254 1.0000
9.500 1.3564 0.01969 0.01224 -0.0640 0.3167 1.0000
9.750 1.3665 0.02031 0.01285 -0.0616 0.3080 1.0000
10.000 1.3782 0.02090 0.01352 -0.0595 0.2984 1.0000
10.250 1.3881 0.02161 0.01426 -0.0573 0.2901 1.0000
10.500 1.3972 0.02238 0.01508 -0.0551 0.2799 1.0000
10.750 1.4050 0.02327 0.01602 -0.0530 0.2684 1.0000
11.000 1.4111 0.02431 0.01708 -0.0508 0.2564 1.0000
11.250 1.4138 0.02561 0.01839 -0.0485 0.2407 1.0000
11.500 1.4155 0.02709 0.01986 -0.0463 0.2246 1.0000
11.750 1.4124 0.02900 0.02172 -0.0441 0.2051 1.0000
12.000 1.4054 0.03137 0.02401 -0.0420 0.1808 1.0000
12.250 1.3927 0.03442 0.02692 -0.0399 0.1529 1.0000
12.500 1.3741 0.03826 0.03059 -0.0382 0.1211 1.0000
12.750 1.3537 0.04259 0.03476 -0.0369 0.0960 1.0000
13.000 1.3422 0.04626 0.03840 -0.0362 0.0840 1.0000
13.250 1.3329 0.04986 0.04201 -0.0356 0.0743 1.0000
13.500 1.3282 0.05310 0.04529 -0.0353 0.0635 1.0000
13.750 1.3198 0.05683 0.04903 -0.0352 0.0489 1.0000
14.000 1.3069 0.06124 0.05340 -0.0353 0.0377 1.0000
14.250 1.2977 0.06533 0.05752 -0.0355 0.0324 1.0000
14.500 1.2898 0.06942 0.06166 -0.0358 0.0290 1.0000
14.750 1.2835 0.07341 0.06573 -0.0363 0.0271 1.0000
15.000 1.2768 0.07755 0.06996 -0.0369 0.0255 1.0000
15.250 1.2724 0.08148 0.07400 -0.0376 0.0243 1.0000
15.500 1.2668 0.08567 0.07828 -0.0384 0.0231 1.0000
15.750 1.2610 0.08996 0.08266 -0.0394 0.0221 1.0000
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