GOE 517 AIRFOIL (goe517-il) Xfoil prediction polar at RE=50,000 Ncrit=9
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Airfoil: GOE 517 AIRFOIL (goe517-il) Reynolds number: 50,000 Max Cl/Cd: 37.39 at α=8.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe517-il-50000.txt Download as CSV file: xf-goe517-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 517 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3640 0.10990 0.10292 -0.0209 1.0000 0.1336
-8.500 -0.3710 0.10904 0.10219 -0.0227 1.0000 0.1367
-8.250 -0.3849 0.10907 0.10238 -0.0245 1.0000 0.1376
-8.000 -0.3567 0.10134 0.09459 -0.0219 1.0000 0.1446
-7.750 -0.3603 0.09953 0.09289 -0.0223 1.0000 0.1494
-7.500 -0.3744 0.09918 0.09272 -0.0241 1.0000 0.1517
-7.250 -0.3604 0.09395 0.08752 -0.0215 1.0000 0.1579
-7.000 -0.3629 0.09200 0.08566 -0.0222 1.0000 0.1640
-6.750 -0.3752 0.09206 0.08584 -0.0269 1.0000 0.1667
-6.500 -0.3597 0.08623 0.08008 -0.0215 1.0000 0.1756
-6.250 -0.3692 0.08614 0.08005 -0.0262 1.0000 0.1811
-6.000 -0.3586 0.08097 0.07499 -0.0211 1.0000 0.1882
-5.750 -0.3641 0.08025 0.07430 -0.0249 1.0000 0.1960
-5.500 -0.3570 0.07593 0.07008 -0.0202 1.0000 0.2031
-5.250 -0.3575 0.07366 0.06782 -0.0209 1.0000 0.2125
-5.000 -0.3553 0.07202 0.06616 -0.0221 1.0000 0.2250
-4.750 -0.3514 0.06855 0.06278 -0.0184 1.0000 0.2358
-4.500 -0.3470 0.06679 0.06096 -0.0200 1.0000 0.2536
-4.250 -0.3430 0.06352 0.05776 -0.0175 1.0000 0.2692
-4.000 -0.3399 0.06051 0.05484 -0.0139 1.0000 0.2898
-3.750 -0.3368 0.05802 0.05240 -0.0114 1.0000 0.3198
-3.500 -0.3368 0.05547 0.04994 -0.0074 1.0000 0.3607
-3.250 -0.3387 0.05305 0.04764 -0.0021 1.0000 0.4082
-3.000 -0.3419 0.05061 0.04531 0.0035 1.0000 0.4601
-2.750 -0.3428 0.04808 0.04286 0.0090 1.0000 0.5042
-2.500 -0.3404 0.04556 0.04043 0.0135 1.0000 0.5429
-2.250 -0.3312 0.04300 0.03787 0.0152 1.0000 0.5743
-2.000 -0.3155 0.04021 0.03508 0.0154 1.0000 0.5929
-1.750 -0.1156 0.03595 0.02747 -0.0324 1.0000 0.1792
-1.500 -0.0872 0.03402 0.02489 -0.0326 1.0000 0.1663
-1.250 -0.0672 0.03236 0.02313 -0.0322 1.0000 0.1727
-1.000 -0.0439 0.03102 0.02137 -0.0318 1.0000 0.1726
-0.750 -0.0214 0.03001 0.01997 -0.0314 1.0000 0.1781
-0.500 -0.0007 0.02921 0.01896 -0.0310 1.0000 0.1917
-0.250 0.0195 0.02848 0.01803 -0.0304 1.0000 0.2033
0.000 0.0431 0.02805 0.01736 -0.0305 0.9995 0.2270
0.250 0.1009 0.02755 0.01670 -0.0364 0.9873 0.2736
0.500 0.1557 0.02708 0.01641 -0.0419 0.9735 0.3393
0.750 0.2260 0.02531 0.01601 -0.0496 0.9584 1.0000
1.000 0.2786 0.02615 0.01628 -0.0546 0.9391 1.0000
1.250 0.3245 0.02684 0.01667 -0.0585 0.9199 1.0000
1.500 0.3719 0.02745 0.01708 -0.0625 0.9021 1.0000
1.750 0.4197 0.02797 0.01745 -0.0664 0.8853 1.0000
2.000 0.4590 0.02843 0.01784 -0.0686 0.8671 1.0000
2.250 0.4975 0.02884 0.01821 -0.0705 0.8485 1.0000
2.500 0.5431 0.02904 0.01839 -0.0732 0.8307 1.0000
2.750 0.5926 0.02900 0.01838 -0.0762 0.8135 1.0000
3.000 0.6319 0.02905 0.01849 -0.0773 0.7951 1.0000
3.250 0.6631 0.02924 0.01873 -0.0771 0.7746 1.0000
3.500 0.7030 0.02903 0.01859 -0.0777 0.7560 1.0000
3.750 0.7354 0.02901 0.01868 -0.0772 0.7359 1.0000
4.000 0.7646 0.02909 0.01882 -0.0762 0.7149 1.0000
4.250 0.8008 0.02875 0.01855 -0.0757 0.6964 1.0000
4.500 0.8226 0.02921 0.01909 -0.0740 0.6744 1.0000
4.750 0.8528 0.02922 0.01923 -0.0730 0.6556 1.0000
5.000 0.8835 0.02924 0.01930 -0.0720 0.6379 1.0000
5.250 0.9023 0.03014 0.02032 -0.0704 0.6182 1.0000
5.500 0.9269 0.03072 0.02101 -0.0692 0.6010 1.0000
5.750 0.9515 0.03138 0.02183 -0.0681 0.5849 1.0000
6.000 0.9751 0.03221 0.02279 -0.0670 0.5696 1.0000
6.250 0.9973 0.03319 0.02393 -0.0658 0.5548 1.0000
6.500 1.0174 0.03440 0.02532 -0.0646 0.5405 1.0000
6.750 1.0365 0.03570 0.02687 -0.0633 0.5263 1.0000
7.000 1.0551 0.03702 0.02842 -0.0619 0.5120 1.0000
7.250 1.0827 0.03680 0.02834 -0.0598 0.4907 1.0000
7.500 1.1096 0.03558 0.02719 -0.0569 0.4603 1.0000
7.750 1.1337 0.03422 0.02594 -0.0537 0.4270 1.0000
8.000 1.1535 0.03196 0.02357 -0.0494 0.3824 1.0000
8.250 1.1612 0.03106 0.02255 -0.0445 0.3311 1.0000
8.500 1.1520 0.03184 0.02295 -0.0381 0.2552 1.0000
8.750 1.1409 0.03389 0.02438 -0.0326 0.1893 1.0000
9.000 1.1429 0.03627 0.02627 -0.0291 0.1543 1.0000
9.250 1.1532 0.03871 0.02857 -0.0267 0.1316 1.0000
9.500 1.1740 0.04140 0.03107 -0.0254 0.1160 1.0000
9.750 1.2006 0.04458 0.03449 -0.0248 0.1059 1.0000
10.000 1.2219 0.04797 0.03802 -0.0240 0.0984 1.0000
10.250 1.2375 0.05144 0.04187 -0.0225 0.0940 1.0000
10.500 1.2521 0.05534 0.04608 -0.0212 0.0917 1.0000
10.750 1.2650 0.05991 0.05087 -0.0202 0.0896 1.0000
11.000 1.2654 0.06439 0.05568 -0.0182 0.0888 1.0000
11.250 1.2546 0.06821 0.05992 -0.0155 0.0885 1.0000
11.500 1.2395 0.07201 0.06405 -0.0128 0.0883 1.0000
11.750 1.2226 0.07597 0.06826 -0.0105 0.0885 1.0000
12.000 1.2035 0.08020 0.07271 -0.0090 0.0887 1.0000
12.250 1.1848 0.08497 0.07765 -0.0085 0.0890 1.0000
12.500 1.0852 0.09536 0.08856 -0.0159 0.0974 1.0000
12.750 1.0563 0.10417 0.09741 -0.0209 0.0993 1.0000
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