GOE 654 AIRFOIL (goe654-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 654 AIRFOIL (goe654-il) Reynolds number: 500,000 Max Cl/Cd: 94.35 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe654-il-500000.txt Download as CSV file: xf-goe654-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 654 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
------ -------- --------- --------- -------- -------- --------
-11.000 -0.1275 0.10366 0.10161 -0.0491 0.9848 0.0305
-10.750 -0.1192 0.09944 0.09738 -0.0520 0.9757 0.0317
-10.500 -0.1343 0.09130 0.08922 -0.0596 0.9683 0.0331
-10.250 -0.1212 0.08593 0.08384 -0.0628 0.9581 0.0335
-10.000 -0.0929 0.08213 0.08001 -0.0670 0.9464 0.0339
-9.750 -0.0637 0.07755 0.07539 -0.0731 0.9323 0.0344
-9.500 -0.0354 0.07257 0.07032 -0.0800 0.9134 0.0355
-9.250 -0.0202 0.06737 0.06499 -0.0858 0.8856 0.0372
-9.000 -0.0564 0.05635 0.05389 -0.0941 0.8637 0.0391
-8.750 -0.0488 0.05414 0.05156 -0.0936 0.8384 0.0394
-8.500 -0.0439 0.05200 0.04933 -0.0932 0.8164 0.0397
-8.250 -0.0399 0.04989 0.04714 -0.0929 0.7969 0.0401
-8.000 -0.0431 0.04680 0.04399 -0.0936 0.7792 0.0403
-7.750 -0.0488 0.04373 0.04088 -0.0945 0.7632 0.0409
-7.500 -0.0754 0.03805 0.03513 -0.0989 0.7503 0.0410
-7.250 -0.0848 0.03330 0.03023 -0.1011 0.7373 0.0417
-7.000 -0.1277 0.02305 0.01912 -0.1031 0.7290 0.0458
-6.750 -0.1098 0.02123 0.01731 -0.1027 0.7130 0.0464
-6.500 -0.0934 0.03252 0.02829 -0.1084 0.7231 0.0469
-6.250 -0.0750 0.03149 0.02716 -0.1075 0.7053 0.0478
-6.000 -0.0572 0.03025 0.02575 -0.1066 0.6881 0.0494
-5.750 -0.0471 0.02752 0.02244 -0.1048 0.6733 0.0542
-5.500 -0.0260 0.02634 0.02120 -0.1042 0.6572 0.0551
-5.250 -0.0048 0.02536 0.02011 -0.1034 0.6420 0.0564
-5.000 0.0138 0.02474 0.01894 -0.1017 0.6288 0.0626
-4.750 0.0358 0.02295 0.01717 -0.1013 0.6174 0.0640
-4.500 0.0538 0.01664 0.00964 -0.0978 0.6096 0.0399
-4.250 0.0795 0.01612 0.00894 -0.0971 0.6007 0.0393
-4.000 0.1052 0.01558 0.00826 -0.0965 0.5924 0.0391
-3.750 0.1309 0.01495 0.00752 -0.0959 0.5852 0.0391
-3.500 0.1567 0.01433 0.00682 -0.0954 0.5782 0.0392
-3.250 0.1819 0.01373 0.00613 -0.0947 0.5724 0.0394
-3.000 0.2079 0.01321 0.00560 -0.0942 0.5668 0.0396
-2.750 0.2333 0.01278 0.00514 -0.0936 0.5610 0.0401
-2.500 0.2587 0.01250 0.00481 -0.0931 0.5556 0.0409
-2.250 0.2849 0.01221 0.00453 -0.0926 0.5503 0.0418
-2.000 0.3108 0.01196 0.00425 -0.0921 0.5452 0.0425
-1.750 0.3367 0.01179 0.00401 -0.0915 0.5404 0.0431
-1.500 0.3630 0.01161 0.00381 -0.0911 0.5359 0.0440
-1.250 0.3896 0.01144 0.00363 -0.0907 0.5310 0.0448
-1.000 0.4157 0.01130 0.00344 -0.0902 0.5260 0.0459
-0.750 0.4419 0.01119 0.00328 -0.0897 0.5211 0.0480
-0.500 0.4687 0.01106 0.00317 -0.0894 0.5160 0.0508
-0.250 0.4952 0.01097 0.00308 -0.0890 0.5108 0.0561
0.250 0.5420 0.00995 0.00304 -0.0876 0.5012 0.3779
0.500 0.5650 0.00958 0.00309 -0.0866 0.4959 0.5179
0.750 0.5861 0.00926 0.00315 -0.0852 0.4906 0.6516
1.000 0.6552 0.00867 0.00334 -0.0934 0.4825 0.9748
1.250 0.7108 0.00879 0.00334 -0.0993 0.4742 1.0000
1.500 0.7343 0.00887 0.00336 -0.0984 0.4678 1.0000
1.750 0.7578 0.00894 0.00338 -0.0974 0.4604 1.0000
2.000 0.7809 0.00905 0.00341 -0.0964 0.4532 1.0000
2.250 0.8045 0.00912 0.00345 -0.0954 0.4444 1.0000
2.500 0.8276 0.00924 0.00349 -0.0944 0.4353 1.0000
2.750 0.8503 0.00937 0.00355 -0.0934 0.4248 1.0000
3.000 0.8735 0.00949 0.00362 -0.0924 0.4137 1.0000
3.250 0.8959 0.00966 0.00371 -0.0913 0.4032 1.0000
3.500 0.9178 0.00986 0.00382 -0.0901 0.3928 1.0000
3.750 0.9406 0.01004 0.00395 -0.0891 0.3832 1.0000
4.000 0.9624 0.01028 0.00410 -0.0879 0.3747 1.0000
4.250 0.9851 0.01048 0.00426 -0.0869 0.3670 1.0000
4.500 1.0066 0.01075 0.00444 -0.0858 0.3604 1.0000
4.750 1.0300 0.01093 0.00462 -0.0849 0.3545 1.0000
5.000 1.0520 0.01118 0.00481 -0.0839 0.3488 1.0000
5.250 1.0739 0.01145 0.00503 -0.0828 0.3438 1.0000
5.500 1.0973 0.01163 0.00523 -0.0820 0.3391 1.0000
5.750 1.1194 0.01188 0.00544 -0.0810 0.3344 1.0000
6.000 1.1400 0.01222 0.00572 -0.0798 0.3296 1.0000
6.250 1.1634 0.01239 0.00592 -0.0790 0.3255 1.0000
6.500 1.1854 0.01260 0.00613 -0.0780 0.3207 1.0000
6.750 1.2059 0.01291 0.00640 -0.0768 0.3161 1.0000
7.000 1.2270 0.01320 0.00668 -0.0757 0.3124 1.0000
7.250 1.2493 0.01339 0.00692 -0.0748 0.3092 1.0000
7.500 1.2705 0.01362 0.00717 -0.0737 0.3056 1.0000
7.750 1.2894 0.01392 0.00744 -0.0723 0.3013 1.0000
8.000 1.3068 0.01424 0.00775 -0.0705 0.2966 1.0000
8.250 1.3262 0.01441 0.00798 -0.0691 0.2925 1.0000
8.500 1.3440 0.01467 0.00825 -0.0675 0.2880 1.0000
8.750 1.3599 0.01504 0.00859 -0.0656 0.2837 1.0000
9.000 1.3781 0.01533 0.00892 -0.0641 0.2802 1.0000
9.250 1.3971 0.01556 0.00921 -0.0628 0.2758 1.0000
9.500 1.4140 0.01590 0.00957 -0.0612 0.2716 1.0000
9.750 1.4280 0.01637 0.01002 -0.0593 0.2671 1.0000
10.000 1.4472 0.01662 0.01035 -0.0582 0.2622 1.0000
10.250 1.4629 0.01701 0.01076 -0.0566 0.2563 1.0000
10.500 1.4761 0.01756 0.01131 -0.0547 0.2514 1.0000
10.750 1.4940 0.01792 0.01174 -0.0536 0.2458 1.0000
11.000 1.5068 0.01852 0.01234 -0.0519 0.2395 1.0000
11.250 1.5211 0.01909 0.01295 -0.0504 0.2323 1.0000
11.500 1.5316 0.01988 0.01373 -0.0487 0.2241 1.0000
11.750 1.5420 0.02074 0.01458 -0.0470 0.2125 1.0000
12.000 1.5501 0.02178 0.01562 -0.0453 0.2015 1.0000
12.250 1.5539 0.02318 0.01696 -0.0434 0.1878 1.0000
12.500 1.5537 0.02494 0.01867 -0.0414 0.1726 1.0000
12.750 1.5534 0.02685 0.02054 -0.0397 0.1599 1.0000
13.000 1.5424 0.02974 0.02332 -0.0377 0.1413 1.0000
13.250 1.5362 0.03241 0.02596 -0.0363 0.1279 1.0000
13.500 1.5287 0.03535 0.02887 -0.0351 0.1158 1.0000
13.750 1.5140 0.03913 0.03259 -0.0341 0.0993 1.0000
14.000 1.4944 0.04362 0.03702 -0.0334 0.0804 1.0000
14.250 1.4681 0.04910 0.04243 -0.0330 0.0598 1.0000
14.500 1.4440 0.05464 0.04796 -0.0331 0.0443 1.0000
14.750 1.4174 0.06066 0.05399 -0.0335 0.0292 1.0000
15.000 1.4016 0.06560 0.05898 -0.0339 0.0246 1.0000
15.250 1.3901 0.07010 0.06357 -0.0345 0.0222 1.0000
15.500 1.3815 0.07433 0.06789 -0.0350 0.0212 1.0000
15.750 1.3736 0.07855 0.07222 -0.0357 0.0205 1.0000
16.000 1.3646 0.08302 0.07679 -0.0366 0.0200 1.0000
16.250 1.3535 0.08788 0.08176 -0.0376 0.0194 1.0000
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