GOE 679 AIRFOIL (goe679-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 679 AIRFOIL (goe679-il) Reynolds number: 200,000 Max Cl/Cd: 54.24 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe679-il-200000-n5.txt Download as CSV file: xf-goe679-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 679 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
------ -------- --------- --------- -------- -------- --------
-15.000 -0.6622 0.08580 0.08069 -0.0727 1.0000 0.0418
-14.750 -0.7113 0.07574 0.07040 -0.0781 1.0000 0.0417
-14.500 -0.7429 0.06878 0.06327 -0.0815 1.0000 0.0418
-14.250 -0.7683 0.06302 0.05737 -0.0840 1.0000 0.0418
-14.000 -0.7890 0.05816 0.05238 -0.0859 1.0000 0.0419
-13.750 -0.8070 0.05362 0.04771 -0.0878 0.9997 0.0420
-13.500 -0.8054 0.04891 0.04281 -0.0933 0.9965 0.0422
-13.250 -0.8001 0.04508 0.03877 -0.0982 0.9929 0.0425
-13.000 -0.7950 0.04199 0.03552 -0.1012 0.9882 0.0427
-12.750 -0.7866 0.03944 0.03278 -0.1038 0.9835 0.0431
-12.500 -0.7741 0.03753 0.03074 -0.1053 0.9797 0.0433
-12.250 -0.7657 0.03599 0.02917 -0.1050 0.9735 0.0436
-12.000 -0.7494 0.03461 0.02775 -0.1057 0.9694 0.0440
-11.750 -0.7425 0.03343 0.02651 -0.1040 0.9618 0.0443
-11.500 -0.7267 0.03228 0.02530 -0.1037 0.9566 0.0447
-11.250 -0.7167 0.03123 0.02420 -0.1019 0.9491 0.0451
-11.000 -0.6984 0.03015 0.02304 -0.1015 0.9435 0.0458
-10.500 -0.6647 0.02818 0.02091 -0.0994 0.9300 0.0470
-10.250 -0.6386 0.02720 0.01981 -0.0999 0.9265 0.0480
-10.000 -0.6285 0.02638 0.01898 -0.0972 0.9167 0.0485
-9.750 -0.6047 0.02543 0.01801 -0.0972 0.9121 0.0493
-9.500 -0.5884 0.02469 0.01722 -0.0955 0.9041 0.0501
-9.250 -0.5667 0.02389 0.01637 -0.0947 0.8979 0.0511
-9.000 -0.5392 0.02307 0.01547 -0.0950 0.8945 0.0523
-8.750 -0.5242 0.02248 0.01481 -0.0927 0.8846 0.0532
-8.500 -0.4975 0.02162 0.01394 -0.0927 0.8794 0.0546
-8.250 -0.4750 0.02093 0.01320 -0.0918 0.8703 0.0563
-8.000 -0.4450 0.02019 0.01238 -0.0921 0.8629 0.0585
-7.750 -0.4158 0.01946 0.01162 -0.0925 0.8553 0.0611
-7.500 -0.3861 0.01883 0.01094 -0.0929 0.8474 0.0651
-7.250 -0.3490 0.01811 0.01020 -0.0948 0.8425 0.0711
-6.750 -0.2839 0.01704 0.00915 -0.0967 0.8275 0.0890
-6.500 -0.2403 0.01658 0.00867 -0.0999 0.8219 0.1017
-6.250 -0.2109 0.01631 0.00838 -0.1001 0.8127 0.1116
-6.000 -0.1678 0.01603 0.00805 -0.1031 0.8054 0.1222
-5.750 -0.1366 0.01583 0.00781 -0.1037 0.7964 0.1302
-5.500 -0.1030 0.01564 0.00755 -0.1047 0.7876 0.1377
-5.250 -0.0714 0.01548 0.00734 -0.1053 0.7790 0.1446
-5.000 -0.0444 0.01535 0.00714 -0.1050 0.7689 0.1507
-4.750 -0.0142 0.01520 0.00695 -0.1053 0.7599 0.1571
-4.500 0.0095 0.01512 0.00680 -0.1043 0.7496 0.1642
-4.250 0.0386 0.01503 0.00669 -0.1044 0.7407 0.1737
-4.000 0.0594 0.01494 0.00659 -0.1028 0.7299 0.1816
-3.750 0.0864 0.01485 0.00645 -0.1025 0.7200 0.1889
-3.500 0.1076 0.01478 0.00630 -0.1009 0.7088 0.1943
-3.250 0.1318 0.01463 0.00615 -0.0999 0.6987 0.1995
-3.000 0.1526 0.01454 0.00604 -0.0983 0.6870 0.2049
-2.750 0.1753 0.01447 0.00589 -0.0970 0.6754 0.2107
-2.500 0.1966 0.01437 0.00577 -0.0955 0.6627 0.2166
-2.250 0.2164 0.01430 0.00567 -0.0936 0.6496 0.2230
-2.000 0.2379 0.01426 0.00555 -0.0921 0.6366 0.2299
-1.750 0.2575 0.01419 0.00546 -0.0902 0.6225 0.2369
-1.500 0.2765 0.01416 0.00539 -0.0882 0.6077 0.2451
-1.250 0.2953 0.01413 0.00531 -0.0861 0.5931 0.2530
-1.000 0.3132 0.01412 0.00525 -0.0839 0.5789 0.2621
-0.750 0.3313 0.01413 0.00519 -0.0818 0.5649 0.2718
-0.500 0.3492 0.01413 0.00517 -0.0796 0.5518 0.2823
-0.250 0.3675 0.01417 0.00514 -0.0775 0.5393 0.2933
0.000 0.3857 0.01420 0.00514 -0.0754 0.5274 0.3055
0.250 0.4046 0.01423 0.00516 -0.0735 0.5167 0.3187
0.750 0.4421 0.01432 0.00525 -0.0697 0.4971 0.3511
1.000 0.4604 0.01438 0.00531 -0.0677 0.4877 0.3714
1.250 0.4791 0.01441 0.00539 -0.0658 0.4791 0.3971
1.500 0.4966 0.01442 0.00549 -0.0637 0.4703 0.4301
1.750 0.5137 0.01442 0.00560 -0.0615 0.4630 0.4770
2.000 0.5291 0.01431 0.00575 -0.0589 0.4553 0.5476
2.250 0.5424 0.01415 0.00592 -0.0558 0.4483 0.6511
2.500 0.6099 0.01411 0.00647 -0.0636 0.4388 0.8628
2.750 0.7143 0.01472 0.00701 -0.0795 0.4270 0.9533
3.000 0.7575 0.01503 0.00727 -0.0827 0.4191 0.9798
3.250 0.7992 0.01542 0.00756 -0.0857 0.4115 0.9987
3.750 0.8317 0.01578 0.00781 -0.0813 0.4002 1.0000
4.000 0.8457 0.01595 0.00793 -0.0787 0.3944 1.0000
4.250 0.8595 0.01617 0.00807 -0.0760 0.3889 1.0000
4.500 0.8749 0.01637 0.00823 -0.0736 0.3837 1.0000
4.750 0.8906 0.01656 0.00841 -0.0713 0.3778 1.0000
5.000 0.9053 0.01680 0.00860 -0.0689 0.3721 1.0000
5.250 0.9203 0.01707 0.00880 -0.0666 0.3668 1.0000
5.500 0.9368 0.01730 0.00903 -0.0645 0.3608 1.0000
5.750 0.9525 0.01756 0.00927 -0.0623 0.3551 1.0000
6.000 0.9674 0.01789 0.00953 -0.0601 0.3500 1.0000
6.250 0.9842 0.01816 0.00981 -0.0582 0.3443 1.0000
6.500 1.0000 0.01847 0.01010 -0.0561 0.3384 1.0000
6.750 1.0143 0.01883 0.01041 -0.0539 0.3329 1.0000
7.000 1.0304 0.01917 0.01076 -0.0520 0.3271 1.0000
7.250 1.0458 0.01954 0.01112 -0.0501 0.3209 1.0000
7.500 1.0596 0.01997 0.01150 -0.0479 0.3155 1.0000
7.750 1.0754 0.02037 0.01192 -0.0461 0.3101 1.0000
8.000 1.0909 0.02080 0.01235 -0.0443 0.3045 1.0000
8.250 1.1045 0.02130 0.01282 -0.0423 0.2993 1.0000
8.500 1.1191 0.02181 0.01331 -0.0405 0.2943 1.0000
8.750 1.1342 0.02231 0.01384 -0.0388 0.2888 1.0000
9.000 1.1473 0.02289 0.01440 -0.0369 0.2836 1.0000
9.250 1.1599 0.02353 0.01501 -0.0351 0.2788 1.0000
9.500 1.1748 0.02411 0.01563 -0.0335 0.2738 1.0000
9.750 1.1878 0.02478 0.01630 -0.0319 0.2689 1.0000
10.000 1.1995 0.02553 0.01703 -0.0301 0.2646 1.0000
10.250 1.2133 0.02623 0.01775 -0.0286 0.2609 1.0000
10.500 1.2265 0.02697 0.01853 -0.0272 0.2561 1.0000
10.750 1.2383 0.02780 0.01936 -0.0256 0.2520 1.0000
11.000 1.2483 0.02874 0.02027 -0.0240 0.2479 1.0000
11.250 1.2610 0.02959 0.02117 -0.0227 0.2440 1.0000
11.500 1.2726 0.03051 0.02214 -0.0214 0.2396 1.0000
11.750 1.2830 0.03153 0.02317 -0.0200 0.2359 1.0000
12.000 1.2925 0.03263 0.02425 -0.0186 0.2325 1.0000
12.250 1.3038 0.03366 0.02531 -0.0175 0.2297 1.0000
12.500 1.3156 0.03469 0.02643 -0.0164 0.2265 1.0000
12.750 1.3257 0.03584 0.02764 -0.0153 0.2233 1.0000
13.000 1.3346 0.03709 0.02890 -0.0142 0.2201 1.0000
13.250 1.3436 0.03836 0.03018 -0.0132 0.2175 1.0000
13.500 1.3526 0.03967 0.03150 -0.0122 0.2147 1.0000
13.750 1.3620 0.04099 0.03293 -0.0113 0.2121 1.0000
14.000 1.3695 0.04248 0.03450 -0.0105 0.2088 1.0000
14.250 1.3764 0.04404 0.03610 -0.0096 0.2058 1.0000
14.500 1.3827 0.04566 0.03774 -0.0088 0.2030 1.0000
14.750 1.3900 0.04720 0.03926 -0.0081 0.2006 1.0000
15.000 1.3964 0.04895 0.04114 -0.0075 0.1982 1.0000
15.250 1.4021 0.05077 0.04307 -0.0070 0.1956 1.0000
15.500 1.4069 0.05269 0.04508 -0.0065 0.1931 1.0000
15.750 1.4117 0.05464 0.04708 -0.0060 0.1907 1.0000
16.000 1.4165 0.05660 0.04908 -0.0056 0.1885 1.0000
16.250 1.4229 0.05837 0.05084 -0.0052 0.1863 1.0000
16.500 1.4251 0.06073 0.05333 -0.0051 0.1841 1.0000
16.750 1.4261 0.06327 0.05601 -0.0050 0.1817 1.0000
17.000 1.4265 0.06590 0.05875 -0.0050 0.1791 1.0000
17.250 1.4271 0.06852 0.06145 -0.0050 0.1767 1.0000
17.500 1.4292 0.07097 0.06392 -0.0051 0.1744 1.0000
17.750 1.4338 0.07307 0.06601 -0.0051 0.1722 1.0000
18.000 1.4274 0.07675 0.06988 -0.0056 0.1696 1.0000
18.250 1.4213 0.08041 0.07369 -0.0062 0.1668 1.0000
18.500 1.4163 0.08394 0.07732 -0.0069 0.1639 1.0000
18.750 1.4150 0.08698 0.08040 -0.0074 0.1612 1.0000
19.000 1.4181 0.08938 0.08278 -0.0078 0.1589 1.0000
19.250 1.4030 0.09446 0.08808 -0.0091 0.1559 1.0000
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Polar data table (+)
Polar graphs
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