GOE 549 AIRFOIL (goe549-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 549 AIRFOIL (goe549-il) Reynolds number: 500,000 Max Cl/Cd: 107.86 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe549-il-500000.txt Download as CSV file: xf-goe549-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 549 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 -0.2613 0.11139 0.10913 -0.0447 1.0000 0.0266
-10.750 -0.2676 0.10694 0.10471 -0.0476 1.0000 0.0279
-10.500 -0.2702 0.10337 0.10119 -0.0487 1.0000 0.0281
-10.250 -0.2590 0.09809 0.09591 -0.0539 0.9910 0.0282
-10.000 -0.2475 0.09309 0.09091 -0.0588 0.9789 0.0282
-9.750 -0.2346 0.08722 0.08502 -0.0653 0.9656 0.0283
-9.500 -0.2266 0.08004 0.07785 -0.0716 0.9552 0.0289
-9.250 -0.1951 0.07660 0.07436 -0.0780 0.9453 0.0295
-9.000 -0.1638 0.07164 0.06933 -0.0872 0.9316 0.0299
-8.750 -0.1362 0.06646 0.06406 -0.0964 0.9112 0.0306
-8.500 -0.1299 0.06137 0.05885 -0.1022 0.8856 0.0310
-8.250 -0.1430 0.05621 0.05362 -0.1058 0.8611 0.0313
-8.000 -0.1752 0.04788 0.04508 -0.1117 0.8383 0.0314
-7.750 -0.1863 0.04311 0.04006 -0.1124 0.8203 0.0319
-7.500 -0.1903 0.03894 0.03560 -0.1121 0.8027 0.0328
-7.250 -0.2205 0.02753 0.02307 -0.1091 0.7867 0.0267
-7.000 -0.2098 0.02454 0.01964 -0.1074 0.7685 0.0265
-6.750 -0.1939 0.02251 0.01719 -0.1059 0.7492 0.0269
-6.500 -0.1736 0.02150 0.01582 -0.1046 0.7301 0.0278
-6.250 -0.1565 0.01937 0.01324 -0.1032 0.7135 0.0290
-6.000 -0.1349 0.01810 0.01181 -0.1025 0.6995 0.0301
-5.750 -0.1110 0.01749 0.01111 -0.1019 0.6880 0.0313
-5.500 -0.0868 0.01687 0.01031 -0.1013 0.6785 0.0326
-5.250 -0.0617 0.01637 0.00966 -0.1008 0.6701 0.0340
-5.000 -0.0357 0.01630 0.00941 -0.1003 0.6631 0.0352
-4.750 -0.0117 0.01503 0.00798 -0.0997 0.6566 0.0365
-4.500 0.0128 0.01422 0.00710 -0.0992 0.6508 0.0380
-4.250 0.0386 0.01380 0.00665 -0.0989 0.6454 0.0395
-4.000 0.0646 0.01342 0.00622 -0.0985 0.6400 0.0410
-3.750 0.0903 0.01301 0.00572 -0.0980 0.6350 0.0415
-3.500 0.1163 0.01263 0.00527 -0.0976 0.6304 0.0419
-3.250 0.1423 0.01227 0.00487 -0.0971 0.6255 0.0423
-3.000 0.1682 0.01199 0.00452 -0.0967 0.6208 0.0427
-2.750 0.1944 0.01177 0.00423 -0.0963 0.6161 0.0431
-2.500 0.2207 0.01151 0.00395 -0.0959 0.6114 0.0436
-2.250 0.2473 0.01134 0.00374 -0.0956 0.6067 0.0442
-2.000 0.2736 0.01114 0.00345 -0.0952 0.6024 0.0453
-1.750 0.3002 0.01094 0.00323 -0.0949 0.5983 0.0466
-1.500 0.3271 0.01079 0.00307 -0.0946 0.5938 0.0484
-1.250 0.3542 0.01069 0.00293 -0.0944 0.5896 0.0509
-0.750 0.4072 0.01033 0.00277 -0.0939 0.5816 0.1214
-0.500 0.4308 0.00973 0.00272 -0.0934 0.5773 0.2927
-0.250 0.4552 0.00936 0.00272 -0.0929 0.5731 0.4150
0.000 0.4791 0.00910 0.00282 -0.0921 0.5692 0.5508
0.250 0.5041 0.00893 0.00286 -0.0915 0.5649 0.6152
0.500 0.5292 0.00881 0.00288 -0.0909 0.5604 0.6678
0.750 0.5531 0.00865 0.00290 -0.0899 0.5561 0.7316
1.000 0.5773 0.00829 0.00299 -0.0888 0.5521 0.8757
1.250 0.6726 0.00827 0.00301 -0.1033 0.5453 1.0000
1.500 0.6971 0.00834 0.00301 -0.1026 0.5406 1.0000
1.750 0.7218 0.00843 0.00305 -0.1020 0.5359 1.0000
2.000 0.7466 0.00848 0.00309 -0.1013 0.5307 1.0000
2.250 0.7713 0.00856 0.00311 -0.1007 0.5256 1.0000
2.500 0.7960 0.00865 0.00316 -0.1000 0.5204 1.0000
2.750 0.8209 0.00871 0.00321 -0.0994 0.5144 1.0000
3.000 0.8454 0.00881 0.00325 -0.0987 0.5091 1.0000
3.250 0.8702 0.00890 0.00333 -0.0981 0.5032 1.0000
3.500 0.8948 0.00898 0.00340 -0.0975 0.4966 1.0000
3.750 0.9190 0.00909 0.00347 -0.0967 0.4895 1.0000
4.000 0.9429 0.00918 0.00353 -0.0960 0.4802 1.0000
4.250 0.9671 0.00930 0.00362 -0.0953 0.4724 1.0000
4.500 0.9904 0.00944 0.00371 -0.0944 0.4630 1.0000
4.750 1.0147 0.00957 0.00383 -0.0938 0.4543 1.0000
5.000 1.0379 0.00975 0.00396 -0.0929 0.4462 1.0000
5.250 1.0620 0.00989 0.00411 -0.0923 0.4374 1.0000
5.500 1.0849 0.01008 0.00426 -0.0914 0.4272 1.0000
6.000 1.1304 0.01048 0.00460 -0.0897 0.4071 1.0000
6.250 1.1527 0.01071 0.00481 -0.0887 0.3984 1.0000
6.500 1.1743 0.01096 0.00502 -0.0877 0.3879 1.0000
6.750 1.1966 0.01118 0.00524 -0.0868 0.3785 1.0000
7.000 1.2174 0.01146 0.00549 -0.0856 0.3689 1.0000
7.250 1.2391 0.01171 0.00573 -0.0846 0.3605 1.0000
7.500 1.2599 0.01199 0.00600 -0.0835 0.3537 1.0000
7.750 1.2809 0.01224 0.00626 -0.0824 0.3458 1.0000
8.000 1.3004 0.01255 0.00657 -0.0811 0.3384 1.0000
8.250 1.3201 0.01283 0.00686 -0.0798 0.3301 1.0000
8.500 1.3378 0.01316 0.00718 -0.0781 0.3234 1.0000
8.750 1.3551 0.01345 0.00749 -0.0764 0.3155 1.0000
9.000 1.3702 0.01381 0.00785 -0.0743 0.3081 1.0000
9.250 1.3873 0.01412 0.00820 -0.0726 0.3011 1.0000
9.500 1.4015 0.01454 0.00861 -0.0705 0.2942 1.0000
9.750 1.4189 0.01487 0.00900 -0.0690 0.2875 1.0000
10.000 1.4318 0.01538 0.00949 -0.0668 0.2800 1.0000
10.250 1.4470 0.01582 0.00997 -0.0651 0.2699 1.0000
10.500 1.4594 0.01639 0.01054 -0.0630 0.2592 1.0000
10.750 1.4701 0.01707 0.01121 -0.0609 0.2484 1.0000
11.000 1.4794 0.01786 0.01199 -0.0586 0.2361 1.0000
11.250 1.4863 0.01884 0.01292 -0.0563 0.2186 1.0000
11.500 1.4890 0.02011 0.01413 -0.0537 0.1980 1.0000
11.750 1.4861 0.02184 0.01573 -0.0508 0.1730 1.0000
12.000 1.4783 0.02404 0.01779 -0.0479 0.1448 1.0000
12.250 1.4633 0.02698 0.02055 -0.0449 0.1130 1.0000
12.500 1.4510 0.02997 0.02344 -0.0426 0.0930 1.0000
12.750 1.4487 0.03235 0.02582 -0.0412 0.0842 1.0000
13.000 1.4453 0.03496 0.02845 -0.0400 0.0757 1.0000
13.250 1.4414 0.03773 0.03124 -0.0390 0.0661 1.0000
13.500 1.4367 0.04069 0.03418 -0.0382 0.0545 1.0000
13.750 1.4279 0.04416 0.03760 -0.0376 0.0417 1.0000
14.000 1.4200 0.04763 0.04107 -0.0370 0.0348 1.0000
14.250 1.4130 0.05110 0.04458 -0.0367 0.0307 1.0000
14.500 1.4089 0.05433 0.04788 -0.0364 0.0285 1.0000
14.750 1.4032 0.05782 0.05143 -0.0363 0.0267 1.0000
15.000 1.3967 0.06150 0.05518 -0.0363 0.0254 1.0000
15.250 1.3928 0.06495 0.05873 -0.0364 0.0248 1.0000
15.500 1.3892 0.06841 0.06230 -0.0366 0.0239 1.0000
15.750 1.3849 0.07206 0.06603 -0.0369 0.0231 1.0000
16.000 1.3796 0.07592 0.06998 -0.0374 0.0225 1.0000
16.250 1.3722 0.08011 0.07427 -0.0380 0.0219 1.0000
16.500 1.3645 0.08444 0.07867 -0.0387 0.0213 1.0000
16.750 1.3535 0.08932 0.08364 -0.0397 0.0207 1.0000
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