GOE 613 AIRFOIL (goe613-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 613 AIRFOIL (goe613-il) Reynolds number: 100,000 Max Cl/Cd: 53.31 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe613-il-100000.txt Download as CSV file: xf-goe613-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 613 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.3670 0.09621 0.09180 -0.0279 1.0000 0.0859
-7.500 -0.3917 0.09550 0.09120 -0.0258 1.0000 0.0866
-7.250 -0.4115 0.09407 0.08986 -0.0267 1.0000 0.0872
-7.000 -0.4300 0.09255 0.08833 -0.0298 1.0000 0.0878
-6.750 -0.4350 0.08845 0.08428 -0.0289 1.0000 0.0887
-6.500 -0.4269 0.08502 0.08095 -0.0225 1.0000 0.0907
-6.250 -0.4271 0.08271 0.07867 -0.0201 1.0000 0.0928
-6.000 -0.4293 0.08027 0.07625 -0.0193 1.0000 0.0957
-5.750 -0.4308 0.07749 0.07343 -0.0212 1.0000 0.1000
-5.500 -0.4302 0.07366 0.06936 -0.0270 1.0000 0.1038
-5.250 -0.4266 0.07069 0.06654 -0.0231 1.0000 0.1059
-5.000 -0.4212 0.06850 0.06436 -0.0212 1.0000 0.1109
-4.750 -0.4101 0.06478 0.06035 -0.0257 1.0000 0.1197
-4.500 -0.3933 0.06194 0.05760 -0.0251 0.9973 0.1248
-4.250 -0.3582 0.05781 0.05324 -0.0313 0.9906 0.1373
-4.000 -0.3233 0.05441 0.04964 -0.0362 0.9842 0.1523
-3.750 -0.2950 0.05160 0.04673 -0.0388 0.9767 0.1688
-3.500 -0.2606 0.04912 0.04403 -0.0428 0.9699 0.1972
-3.250 -0.2346 0.04655 0.04150 -0.0438 0.9621 0.2165
-3.000 -0.2049 0.04436 0.03926 -0.0456 0.9549 0.2481
-2.000 -0.0470 0.03435 0.02780 -0.0581 0.9223 0.2449
-1.750 0.0216 0.03019 0.02185 -0.0606 0.9173 0.1111
-1.500 0.0594 0.02887 0.02022 -0.0619 0.9067 0.1101
-1.250 0.1133 0.02731 0.01825 -0.0656 0.9002 0.1065
-1.000 0.1486 0.02628 0.01704 -0.0663 0.8882 0.1055
-0.750 0.1869 0.02524 0.01595 -0.0676 0.8781 0.1064
-0.500 0.2362 0.02406 0.01480 -0.0708 0.8713 0.1116
-0.250 0.2700 0.02337 0.01408 -0.0713 0.8596 0.1174
0.000 0.3230 0.02195 0.01281 -0.0750 0.8551 0.1259
0.250 0.3563 0.02120 0.01207 -0.0752 0.8429 0.1392
0.500 0.4635 0.01774 0.01084 -0.0894 0.8422 1.0000
0.750 0.4989 0.01737 0.01026 -0.0900 0.8292 1.0000
1.000 0.5350 0.01695 0.00969 -0.0906 0.8160 1.0000
1.250 0.5707 0.01652 0.00914 -0.0912 0.8022 1.0000
1.500 0.6053 0.01612 0.00863 -0.0916 0.7871 1.0000
1.750 0.6390 0.01576 0.00816 -0.0918 0.7707 1.0000
2.000 0.6725 0.01545 0.00773 -0.0920 0.7531 1.0000
2.250 0.7006 0.01532 0.00748 -0.0913 0.7324 1.0000
2.500 0.7281 0.01526 0.00729 -0.0905 0.7101 1.0000
2.750 0.7538 0.01528 0.00718 -0.0895 0.6865 1.0000
3.000 0.7791 0.01534 0.00710 -0.0884 0.6621 1.0000
3.250 0.8009 0.01550 0.00715 -0.0868 0.6361 1.0000
3.500 0.8239 0.01570 0.00718 -0.0855 0.6110 1.0000
3.750 0.8480 0.01594 0.00724 -0.0844 0.5871 1.0000
4.000 0.8698 0.01632 0.00747 -0.0830 0.5628 1.0000
4.250 0.8945 0.01678 0.00769 -0.0821 0.5421 1.0000
4.500 0.9164 0.01730 0.00813 -0.0810 0.5219 1.0000
4.750 0.9395 0.01786 0.00859 -0.0800 0.5038 1.0000
5.000 0.9625 0.01841 0.00906 -0.0791 0.4876 1.0000
5.250 0.9855 0.01897 0.00957 -0.0782 0.4730 1.0000
5.500 1.0086 0.01955 0.01011 -0.0774 0.4599 1.0000
5.750 1.0323 0.02012 0.01066 -0.0766 0.4479 1.0000
6.000 1.0566 0.02067 0.01116 -0.0760 0.4366 1.0000
6.250 1.0773 0.02123 0.01181 -0.0748 0.4252 1.0000
6.500 1.0992 0.02180 0.01245 -0.0738 0.4144 1.0000
6.750 1.1231 0.02236 0.01297 -0.0731 0.4044 1.0000
7.000 1.1443 0.02291 0.01360 -0.0720 0.3942 1.0000
7.250 1.1640 0.02343 0.01420 -0.0706 0.3829 1.0000
7.500 1.1830 0.02381 0.01461 -0.0690 0.3698 1.0000
7.750 1.2014 0.02416 0.01497 -0.0674 0.3566 1.0000
8.000 1.2198 0.02452 0.01532 -0.0657 0.3437 1.0000
8.250 1.2391 0.02491 0.01568 -0.0643 0.3315 1.0000
8.500 1.2540 0.02531 0.01623 -0.0621 0.3197 1.0000
8.750 1.2694 0.02576 0.01685 -0.0601 0.3085 1.0000
9.000 1.2832 0.02611 0.01727 -0.0578 0.2962 1.0000
9.250 1.2972 0.02645 0.01767 -0.0555 0.2847 1.0000
9.500 1.3078 0.02673 0.01800 -0.0527 0.2722 1.0000
9.750 1.3124 0.02698 0.01838 -0.0489 0.2582 1.0000
10.000 1.3176 0.02734 0.01896 -0.0452 0.2457 1.0000
10.250 1.3190 0.02774 0.01949 -0.0410 0.2315 1.0000
10.500 1.3192 0.02830 0.02012 -0.0369 0.2142 1.0000
10.750 1.3179 0.02912 0.02100 -0.0330 0.1868 1.0000
11.000 1.3136 0.03059 0.02229 -0.0293 0.1397 1.0000
11.250 1.2995 0.03322 0.02449 -0.0254 0.0917 1.0000
11.500 1.2879 0.03601 0.02706 -0.0222 0.0669 1.0000
11.750 1.2785 0.03879 0.02979 -0.0196 0.0579 1.0000
12.000 1.2703 0.04161 0.03268 -0.0175 0.0537 1.0000
12.250 1.2595 0.04484 0.03599 -0.0158 0.0513 1.0000
12.500 1.2520 0.04799 0.03932 -0.0147 0.0495 1.0000
12.750 1.2432 0.05149 0.04300 -0.0140 0.0482 1.0000
13.000 1.2324 0.05543 0.04713 -0.0138 0.0469 1.0000
13.250 1.2222 0.05956 0.05142 -0.0141 0.0462 1.0000
13.500 1.2108 0.06409 0.05609 -0.0147 0.0453 1.0000
13.750 1.2018 0.06849 0.06063 -0.0155 0.0448 1.0000
14.000 1.1940 0.07278 0.06502 -0.0163 0.0441 1.0000
14.250 1.1885 0.07663 0.06892 -0.0167 0.0432 1.0000
14.500 1.1926 0.07869 0.07095 -0.0155 0.0420 1.0000
14.750 1.1991 0.08090 0.07328 -0.0150 0.0410 1.0000
15.000 1.2054 0.08322 0.07572 -0.0145 0.0399 1.0000
15.250 1.2130 0.08540 0.07800 -0.0138 0.0387 1.0000
15.500 1.2240 0.08719 0.07993 -0.0128 0.0380 1.0000
15.750 1.2339 0.08939 0.08227 -0.0120 0.0376 1.0000
16.000 1.2399 0.09234 0.08540 -0.0117 0.0374 1.0000
16.250 1.2411 0.09608 0.08935 -0.0121 0.0373 1.0000
16.500 1.2365 0.10073 0.09423 -0.0134 0.0375 1.0000
16.750 1.2261 0.10641 0.10016 -0.0157 0.0377 1.0000
17.000 1.2115 0.11290 0.10689 -0.0188 0.0380 1.0000
17.250 1.1935 0.12021 0.11445 -0.0229 0.0383 1.0000
17.500 1.1722 0.12850 0.12297 -0.0279 0.0388 1.0000
17.750 1.1484 0.13780 0.13249 -0.0338 0.0393 1.0000
18.000 1.1201 0.14874 0.14362 -0.0410 0.0399 1.0000
18.250 1.0892 0.16124 0.15622 -0.0492 0.0408 1.0000
18.500 1.0625 0.17359 0.16863 -0.0568 0.0417 1.0000
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