GOE 645 AIRFOIL (goe645-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 645 AIRFOIL (goe645-il) Reynolds number: 200,000 Max Cl/Cd: 65.82 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe645-il-200000-n5.txt Download as CSV file: xf-goe645-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 645 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
------ -------- --------- --------- -------- -------- --------
-13.750 -0.6348 0.06967 0.06504 -0.0713 1.0000 0.0329
-13.500 -0.6587 0.06328 0.05855 -0.0753 1.0000 0.0330
-13.250 -0.6749 0.05826 0.05346 -0.0783 1.0000 0.0333
-13.000 -0.6928 0.05316 0.04827 -0.0814 1.0000 0.0334
-12.750 -0.7082 0.04857 0.04359 -0.0842 1.0000 0.0336
-12.500 -0.7251 0.04406 0.03898 -0.0871 1.0000 0.0338
-12.250 -0.7486 0.04026 0.03507 -0.0886 1.0000 0.0339
-12.000 -0.7690 0.03839 0.03313 -0.0854 1.0000 0.0340
-11.750 -0.7738 0.03664 0.03129 -0.0836 0.9991 0.0344
-11.500 -0.7479 0.03435 0.02881 -0.0873 0.9913 0.0353
-11.250 -0.7216 0.03227 0.02647 -0.0903 0.9830 0.0364
-11.000 -0.6963 0.03046 0.02436 -0.0924 0.9727 0.0374
-10.750 -0.6701 0.02902 0.02292 -0.0937 0.9623 0.0382
-10.500 -0.6421 0.02778 0.02163 -0.0950 0.9522 0.0391
-10.250 -0.6114 0.02654 0.02028 -0.0968 0.9427 0.0402
-10.000 -0.5821 0.02539 0.01899 -0.0982 0.9312 0.0414
-9.750 -0.5501 0.02429 0.01769 -0.0998 0.9204 0.0427
-9.500 -0.5171 0.02313 0.01644 -0.1016 0.9095 0.0437
-9.250 -0.4864 0.02214 0.01540 -0.1029 0.8958 0.0449
-9.000 -0.4553 0.02128 0.01444 -0.1040 0.8818 0.0463
-8.750 -0.4251 0.02050 0.01352 -0.1049 0.8674 0.0478
-8.500 -0.3960 0.01983 0.01267 -0.1053 0.8529 0.0492
-8.250 -0.3706 0.01907 0.01184 -0.1052 0.8385 0.0505
-8.000 -0.3464 0.01845 0.01112 -0.1048 0.8242 0.0520
-7.750 -0.3217 0.01792 0.01047 -0.1043 0.8112 0.0540
-7.500 -0.2966 0.01746 0.00986 -0.1037 0.7989 0.0561
-7.250 -0.2730 0.01693 0.00925 -0.1030 0.7867 0.0585
-7.000 -0.2489 0.01646 0.00870 -0.1023 0.7753 0.0615
-6.750 -0.2239 0.01606 0.00819 -0.1017 0.7646 0.0653
-6.500 -0.1996 0.01565 0.00778 -0.1010 0.7532 0.0720
-6.250 -0.1744 0.01532 0.00747 -0.1005 0.7429 0.0846
-6.000 -0.1486 0.01509 0.00717 -0.0999 0.7324 0.0993
-5.750 -0.1228 0.01487 0.00687 -0.0993 0.7221 0.1098
-5.500 -0.0966 0.01471 0.00657 -0.0987 0.7118 0.1186
-5.250 -0.0713 0.01447 0.00631 -0.0981 0.7011 0.1268
-5.000 -0.0451 0.01432 0.00606 -0.0976 0.6914 0.1347
-4.750 -0.0195 0.01411 0.00585 -0.0970 0.6806 0.1436
-4.500 0.0064 0.01396 0.00565 -0.0965 0.6702 0.1522
-4.250 0.0324 0.01383 0.00547 -0.0959 0.6592 0.1618
-4.000 0.0584 0.01371 0.00534 -0.0953 0.6483 0.1731
-3.750 0.0845 0.01362 0.00522 -0.0948 0.6381 0.1874
-3.500 0.1107 0.01355 0.00515 -0.0942 0.6267 0.2033
-3.250 0.1369 0.01352 0.00508 -0.0937 0.6158 0.2177
-3.000 0.1631 0.01351 0.00499 -0.0931 0.6046 0.2297
-2.750 0.1895 0.01349 0.00491 -0.0926 0.5937 0.2396
-2.500 0.2157 0.01349 0.00483 -0.0920 0.5839 0.2481
-2.250 0.2420 0.01349 0.00477 -0.0915 0.5734 0.2567
-2.000 0.2683 0.01351 0.00470 -0.0909 0.5636 0.2643
-1.750 0.2944 0.01353 0.00467 -0.0904 0.5540 0.2718
-1.500 0.3209 0.01357 0.00461 -0.0898 0.5446 0.2793
-1.250 0.3465 0.01360 0.00458 -0.0892 0.5347 0.2856
-1.000 0.3725 0.01363 0.00457 -0.0886 0.5239 0.2926
-0.750 0.3981 0.01370 0.00453 -0.0880 0.5136 0.2995
-0.500 0.4236 0.01373 0.00454 -0.0874 0.5029 0.3071
-0.250 0.4495 0.01380 0.00454 -0.0868 0.4941 0.3157
0.000 0.4751 0.01383 0.00458 -0.0862 0.4858 0.3240
0.250 0.5008 0.01390 0.00460 -0.0857 0.4778 0.3320
0.500 0.5263 0.01394 0.00462 -0.0851 0.4692 0.3388
0.750 0.5515 0.01401 0.00466 -0.0844 0.4612 0.3471
1.000 0.5769 0.01406 0.00471 -0.0838 0.4525 0.3566
1.250 0.6018 0.01414 0.00477 -0.0831 0.4454 0.3677
1.500 0.6273 0.01416 0.00485 -0.0826 0.4382 0.3785
1.750 0.6521 0.01423 0.00492 -0.0819 0.4312 0.3915
2.000 0.6770 0.01429 0.00501 -0.0812 0.4244 0.4066
2.250 0.7015 0.01433 0.00511 -0.0805 0.4171 0.4250
2.500 0.7251 0.01438 0.00522 -0.0797 0.4106 0.4499
2.750 0.7491 0.01436 0.00536 -0.0789 0.4036 0.4895
3.000 0.7715 0.01431 0.00550 -0.0778 0.3968 0.5569
3.250 0.7929 0.01387 0.00568 -0.0762 0.3911 0.7577
3.750 0.8820 0.01414 0.00610 -0.0831 0.3751 1.0000
4.000 0.9052 0.01434 0.00626 -0.0822 0.3676 1.0000
4.250 0.9269 0.01458 0.00642 -0.0810 0.3600 1.0000
4.500 0.9497 0.01479 0.00660 -0.0801 0.3516 1.0000
4.750 0.9710 0.01505 0.00679 -0.0788 0.3441 1.0000
5.000 0.9935 0.01528 0.00701 -0.0779 0.3367 1.0000
5.250 1.0145 0.01555 0.00723 -0.0766 0.3297 1.0000
5.500 1.0364 0.01581 0.00747 -0.0756 0.3230 1.0000
5.750 1.0571 0.01609 0.00773 -0.0743 0.3161 1.0000
6.000 1.0775 0.01639 0.00800 -0.0730 0.3098 1.0000
6.250 1.0979 0.01668 0.00828 -0.0717 0.3032 1.0000
6.500 1.1166 0.01703 0.00859 -0.0702 0.2975 1.0000
6.750 1.1367 0.01733 0.00890 -0.0689 0.2919 1.0000
7.000 1.1549 0.01767 0.00923 -0.0673 0.2863 1.0000
7.250 1.1706 0.01805 0.00959 -0.0653 0.2816 1.0000
7.500 1.1885 0.01839 0.00995 -0.0637 0.2771 1.0000
7.750 1.2050 0.01877 0.01034 -0.0619 0.2721 1.0000
8.000 1.2193 0.01923 0.01078 -0.0598 0.2668 1.0000
8.250 1.2355 0.01966 0.01123 -0.0581 0.2629 1.0000
8.500 1.2523 0.02009 0.01170 -0.0565 0.2590 1.0000
8.750 1.2678 0.02057 0.01220 -0.0548 0.2551 1.0000
9.000 1.2819 0.02112 0.01277 -0.0530 0.2513 1.0000
9.250 1.2958 0.02170 0.01336 -0.0512 0.2475 1.0000
9.500 1.3115 0.02223 0.01396 -0.0497 0.2438 1.0000
9.750 1.3258 0.02284 0.01461 -0.0482 0.2399 1.0000
10.000 1.3388 0.02353 0.01534 -0.0465 0.2364 1.0000
10.250 1.3496 0.02434 0.01616 -0.0448 0.2327 1.0000
10.500 1.3632 0.02506 0.01695 -0.0434 0.2285 1.0000
10.750 1.3760 0.02586 0.01782 -0.0420 0.2246 1.0000
11.000 1.3867 0.02679 0.01880 -0.0406 0.2205 1.0000
11.250 1.3944 0.02793 0.01995 -0.0390 0.2162 1.0000
11.500 1.4064 0.02889 0.02100 -0.0378 0.2123 1.0000
11.750 1.4169 0.02996 0.02216 -0.0367 0.2080 1.0000
12.000 1.4245 0.03127 0.02352 -0.0355 0.2035 1.0000
12.250 1.4305 0.03274 0.02503 -0.0343 0.1995 1.0000
12.500 1.4407 0.03398 0.02638 -0.0334 0.1951 1.0000
12.750 1.4471 0.03554 0.02802 -0.0325 0.1899 1.0000
13.000 1.4499 0.03742 0.02994 -0.0315 0.1852 1.0000
13.250 1.4568 0.03905 0.03169 -0.0308 0.1789 1.0000
13.500 1.4573 0.04128 0.03396 -0.0301 0.1723 1.0000
13.750 1.4596 0.04345 0.03619 -0.0295 0.1649 1.0000
14.000 1.4570 0.04614 0.03892 -0.0291 0.1582 1.0000
14.250 1.4547 0.04891 0.04173 -0.0288 0.1519 1.0000
14.500 1.4491 0.05215 0.04500 -0.0287 0.1468 1.0000
14.750 1.4446 0.05537 0.04826 -0.0287 0.1428 1.0000
15.000 1.4390 0.05882 0.05176 -0.0289 0.1395 1.0000
15.250 1.4330 0.06241 0.05541 -0.0292 0.1369 1.0000
15.500 1.4291 0.06581 0.05887 -0.0296 0.1347 1.0000
15.750 1.4259 0.06918 0.06232 -0.0300 0.1325 1.0000
16.000 1.4236 0.07249 0.06571 -0.0305 0.1306 1.0000
16.250 1.4203 0.07598 0.06927 -0.0311 0.1288 1.0000
16.500 1.4166 0.07954 0.07289 -0.0317 0.1271 1.0000
16.750 1.4143 0.08292 0.07632 -0.0324 0.1255 1.0000
17.000 1.4132 0.08614 0.07957 -0.0330 0.1240 1.0000
17.250 1.4127 0.08939 0.08293 -0.0337 0.1222 1.0000
17.500 1.4116 0.09278 0.08644 -0.0345 0.1205 1.0000
17.750 1.4083 0.09652 0.09028 -0.0356 0.1181 1.0000
18.000 1.4064 0.10004 0.09387 -0.0366 0.1162 1.0000
18.250 1.4043 0.10356 0.09743 -0.0376 0.1138 1.0000
18.500 1.4066 0.10626 0.10009 -0.0383 0.1113 1.0000
18.750 1.4042 0.11006 0.10403 -0.0396 0.1095 1.0000
19.000 1.3998 0.11420 0.10834 -0.0412 0.1076 1.0000
19.250 1.3951 0.11841 0.11267 -0.0429 0.1054 1.0000
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Polar data table (+)
Polar graphs
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