GOE 403 AIRFOIL (goe403-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: GOE 403 AIRFOIL (goe403-il) Reynolds number: 50,000 Max Cl/Cd: 41.89 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe403-il-50000-n5.txt Download as CSV file: xf-goe403-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 403 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3457 0.10486 0.09834 -0.0271 1.0000 0.0819
-7.750 -0.3518 0.10366 0.09728 -0.0283 1.0000 0.0825
-7.500 -0.3541 0.10192 0.09566 -0.0308 1.0000 0.0829
-7.250 -0.3472 0.09722 0.09104 -0.0295 1.0000 0.0840
-7.000 -0.3394 0.09318 0.08703 -0.0278 1.0000 0.0857
-6.750 -0.3359 0.09022 0.08415 -0.0279 1.0000 0.0869
-6.500 -0.3329 0.08731 0.08132 -0.0285 1.0000 0.0880
-6.250 -0.3298 0.08450 0.07859 -0.0294 1.0000 0.0885
-6.000 -0.3263 0.08156 0.07568 -0.0305 1.0000 0.0883
-5.750 -0.3158 0.07616 0.07027 -0.0368 1.0000 0.0542
-5.500 -0.3115 0.07291 0.06707 -0.0360 1.0000 0.0525
-5.250 -0.3043 0.06964 0.06377 -0.0373 1.0000 0.0520
-5.000 -0.2944 0.06621 0.06032 -0.0392 1.0000 0.0524
-4.750 -0.2811 0.06252 0.05655 -0.0418 1.0000 0.0531
-4.500 -0.2648 0.05858 0.05249 -0.0445 1.0000 0.0535
-4.250 -0.2469 0.05454 0.04830 -0.0469 1.0000 0.0533
-4.000 -0.2256 0.05031 0.04385 -0.0496 1.0000 0.0532
-3.750 -0.1972 0.04540 0.03851 -0.0534 1.0000 0.0546
-3.500 -0.1655 0.04266 0.03562 -0.0567 0.9945 0.0626
-3.250 -0.1180 0.03735 0.02956 -0.0629 0.9879 0.0656
-3.000 -0.0772 0.03458 0.02627 -0.0669 0.9800 0.0777
-2.750 -0.0338 0.03092 0.02167 -0.0706 0.9728 0.0808
-2.500 0.0079 0.02836 0.01843 -0.0735 0.9656 0.0854
-2.250 0.0464 0.02703 0.01652 -0.0758 0.9561 0.0967
-2.000 0.0831 0.02587 0.01516 -0.0779 0.9462 0.1053
-1.750 0.1231 0.02455 0.01327 -0.0799 0.9375 0.1113
-1.500 0.1622 0.02359 0.01210 -0.0819 0.9280 0.1196
-1.250 0.2002 0.02277 0.01106 -0.0836 0.9174 0.1332
-1.000 0.2390 0.02212 0.01031 -0.0857 0.9070 0.1632
-0.750 0.2797 0.02139 0.00966 -0.0881 0.8975 0.2084
-0.500 0.3156 0.02063 0.00918 -0.0897 0.8859 0.2790
-0.250 0.3528 0.01832 0.00865 -0.0911 0.8748 1.0000
0.000 0.3882 0.01837 0.00826 -0.0921 0.8615 1.0000
0.250 0.4222 0.01843 0.00801 -0.0929 0.8479 1.0000
0.500 0.4550 0.01849 0.00783 -0.0934 0.8337 1.0000
0.750 0.4865 0.01858 0.00773 -0.0937 0.8192 1.0000
1.000 0.5169 0.01868 0.00768 -0.0938 0.8043 1.0000
1.250 0.5461 0.01881 0.00769 -0.0937 0.7890 1.0000
1.500 0.5745 0.01896 0.00774 -0.0934 0.7737 1.0000
1.750 0.6005 0.01917 0.00789 -0.0928 0.7571 1.0000
2.000 0.6266 0.01939 0.00810 -0.0922 0.7406 1.0000
2.250 0.6529 0.01961 0.00830 -0.0916 0.7247 1.0000
2.500 0.6791 0.01984 0.00853 -0.0911 0.7093 1.0000
2.750 0.7053 0.02008 0.00882 -0.0905 0.6944 1.0000
3.000 0.7315 0.02034 0.00912 -0.0900 0.6800 1.0000
3.250 0.7576 0.02061 0.00945 -0.0894 0.6660 1.0000
3.500 0.7836 0.02091 0.00984 -0.0888 0.6524 1.0000
3.750 0.8096 0.02123 0.01032 -0.0883 0.6391 1.0000
4.000 0.8356 0.02158 0.01081 -0.0877 0.6264 1.0000
4.250 0.8617 0.02194 0.01135 -0.0871 0.6139 1.0000
4.500 0.8853 0.02193 0.01137 -0.0853 0.5886 1.0000
4.750 0.9046 0.02197 0.01146 -0.0827 0.5526 1.0000
5.000 0.9224 0.02210 0.01151 -0.0798 0.5094 1.0000
5.250 0.9401 0.02244 0.01187 -0.0774 0.4676 1.0000
5.500 0.9542 0.02291 0.01224 -0.0744 0.4049 1.0000
5.750 0.9613 0.02418 0.01268 -0.0710 0.2504 1.0000
6.000 0.9573 0.02827 0.01504 -0.0681 0.0492 1.0000
6.250 0.9727 0.02990 0.01680 -0.0664 0.0407 1.0000
6.500 0.9866 0.03158 0.01879 -0.0646 0.0371 1.0000
6.750 0.9990 0.03325 0.02072 -0.0627 0.0350 1.0000
7.000 1.0098 0.03496 0.02269 -0.0607 0.0327 1.0000
7.250 1.0173 0.03685 0.02478 -0.0585 0.0305 1.0000
7.500 1.0204 0.03901 0.02707 -0.0560 0.0290 1.0000
7.750 1.0246 0.04096 0.02918 -0.0534 0.0283 1.0000
8.000 1.0318 0.04287 0.03128 -0.0510 0.0279 1.0000
8.250 1.0447 0.04472 0.03332 -0.0490 0.0276 1.0000
8.500 1.0712 0.04658 0.03538 -0.0475 0.0272 1.0000
8.750 1.1137 0.04907 0.03811 -0.0476 0.0267 1.0000
9.000 1.1431 0.05192 0.04142 -0.0470 0.0258 1.0000
9.250 1.1631 0.05498 0.04486 -0.0459 0.0250 1.0000
9.500 1.1768 0.05822 0.04848 -0.0445 0.0247 1.0000
9.750 1.1854 0.06163 0.05228 -0.0428 0.0248 1.0000
10.000 1.1887 0.06510 0.05611 -0.0409 0.0251 1.0000
10.250 1.1862 0.06851 0.05985 -0.0387 0.0254 1.0000
10.500 1.1792 0.07200 0.06364 -0.0367 0.0256 1.0000
10.750 1.1689 0.07562 0.06754 -0.0352 0.0259 1.0000
11.000 1.1563 0.07957 0.07175 -0.0344 0.0261 1.0000
11.250 1.1421 0.08385 0.07627 -0.0345 0.0263 1.0000
11.500 1.1270 0.08852 0.08117 -0.0353 0.0265 1.0000
11.750 1.1108 0.09367 0.08651 -0.0371 0.0266 1.0000
12.000 1.0939 0.09934 0.09237 -0.0396 0.0268 1.0000
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Polar data table (+)
Polar graphs
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