GOE 478 AIRFOIL (goe478-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: GOE 478 AIRFOIL (goe478-il) Reynolds number: 100,000 Max Cl/Cd: 53 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe478-il-100000-n5.txt Download as CSV file: xf-goe478-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 478 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.2844 0.13024 0.12459 -0.0439 1.0000 0.0787
-11.250 -0.2975 0.12810 0.12252 -0.0457 1.0000 0.0793
-11.000 -0.2995 0.12531 0.11981 -0.0458 1.0000 0.0796
-10.750 -0.2864 0.12239 0.11692 -0.0437 1.0000 0.0803
-10.500 -0.2833 0.12015 0.11474 -0.0425 1.0000 0.0809
-10.250 -0.2841 0.11817 0.11283 -0.0411 1.0000 0.0816
-10.000 -0.2893 0.11654 0.11128 -0.0393 1.0000 0.0821
-9.500 -0.2862 0.10374 0.09843 -0.0513 0.9887 0.0640
-9.250 -0.2645 0.10068 0.09535 -0.0529 0.9842 0.0615
-8.750 -0.2661 0.08720 0.08183 -0.0666 0.9669 0.0567
-8.500 -0.2554 0.08306 0.07770 -0.0706 0.9595 0.0565
-8.250 -0.2456 0.07922 0.07385 -0.0740 0.9513 0.0561
-8.000 -0.2364 0.07456 0.06918 -0.0792 0.9439 0.0555
-7.750 -0.2368 0.06937 0.06397 -0.0846 0.9326 0.0549
-7.500 -0.2348 0.06172 0.05618 -0.0931 0.9241 0.0541
-7.250 -0.2434 0.05338 0.04755 -0.0989 0.9131 0.0533
-7.000 -0.2542 0.04552 0.03918 -0.1014 0.9031 0.0529
-6.750 -0.2472 0.04102 0.03423 -0.1022 0.8959 0.0535
-6.500 -0.2291 0.03704 0.02971 -0.1037 0.8916 0.0546
-6.250 -0.2230 0.03454 0.02677 -0.1014 0.8814 0.0553
-6.000 -0.2009 0.03178 0.02346 -0.1016 0.8761 0.0560
-5.750 -0.1772 0.02965 0.02083 -0.1016 0.8711 0.0566
-5.500 -0.1594 0.02852 0.01955 -0.1000 0.8632 0.0572
-5.250 -0.1308 0.02736 0.01827 -0.1004 0.8584 0.0581
-5.000 -0.0981 0.02619 0.01695 -0.1014 0.8547 0.0593
-4.750 -0.0813 0.02553 0.01615 -0.0994 0.8461 0.0608
-4.500 -0.0529 0.02453 0.01492 -0.0994 0.8405 0.0629
-4.250 -0.0202 0.02360 0.01390 -0.1002 0.8366 0.0647
-4.000 -0.0011 0.02315 0.01345 -0.0986 0.8295 0.0662
-3.750 0.0247 0.02253 0.01275 -0.0981 0.8239 0.0681
-3.500 0.0556 0.02179 0.01189 -0.0984 0.8197 0.0707
-3.250 0.0805 0.02137 0.01151 -0.0978 0.8141 0.0735
-3.000 0.1031 0.02104 0.01116 -0.0966 0.8073 0.0774
-2.750 0.1327 0.02055 0.01067 -0.0967 0.8023 0.0822
-2.500 0.1610 0.02012 0.01018 -0.0965 0.7972 0.0883
-2.250 0.1816 0.01986 0.00998 -0.0950 0.7895 0.0955
-2.000 0.2108 0.01940 0.00953 -0.0950 0.7840 0.1080
-1.750 0.2370 0.01902 0.00919 -0.0944 0.7779 0.1243
-1.500 0.2590 0.01878 0.00910 -0.0932 0.7701 0.1428
-1.250 0.2902 0.01850 0.00886 -0.0935 0.7644 0.1687
-1.000 0.3127 0.01839 0.00881 -0.0923 0.7562 0.1913
-0.750 0.3393 0.01819 0.00862 -0.0917 0.7487 0.2180
-0.500 0.3692 0.01783 0.00838 -0.0919 0.7425 0.2535
-0.250 0.3890 0.01761 0.00836 -0.0903 0.7328 0.2902
0.000 0.4200 0.01707 0.00811 -0.0907 0.7260 0.3677
0.250 0.4356 0.01642 0.00823 -0.0881 0.7158 0.5721
0.500 0.5270 0.01564 0.00820 -0.0991 0.7085 0.9470
0.750 0.5856 0.01569 0.00812 -0.1052 0.6983 0.9981
1.000 0.6112 0.01571 0.00800 -0.1045 0.6886 1.0000
1.250 0.6281 0.01585 0.00806 -0.1022 0.6764 1.0000
1.500 0.6509 0.01589 0.00797 -0.1010 0.6663 1.0000
1.750 0.6689 0.01602 0.00803 -0.0989 0.6538 1.0000
2.000 0.6878 0.01614 0.00809 -0.0970 0.6415 1.0000
2.250 0.7093 0.01622 0.00807 -0.0955 0.6302 1.0000
2.500 0.7298 0.01633 0.00810 -0.0939 0.6183 1.0000
2.750 0.7498 0.01648 0.00819 -0.0922 0.6065 1.0000
3.000 0.7723 0.01659 0.00820 -0.0909 0.5961 1.0000
3.250 0.7947 0.01672 0.00823 -0.0896 0.5858 1.0000
3.500 0.8166 0.01689 0.00833 -0.0883 0.5756 1.0000
3.750 0.8414 0.01702 0.00832 -0.0874 0.5668 1.0000
4.000 0.8622 0.01725 0.00850 -0.0860 0.5561 1.0000
4.250 0.8854 0.01746 0.00859 -0.0849 0.5458 1.0000
4.500 0.9077 0.01770 0.00872 -0.0836 0.5345 1.0000
4.750 0.9285 0.01799 0.00896 -0.0822 0.5235 1.0000
5.250 0.9721 0.01861 0.00945 -0.0797 0.5037 1.0000
5.500 0.9969 0.01892 0.00965 -0.0790 0.4948 1.0000
5.750 1.0144 0.01928 0.01006 -0.0771 0.4849 1.0000
6.000 1.0382 0.01961 0.01030 -0.0762 0.4759 1.0000
6.250 1.0544 0.01998 0.01073 -0.0741 0.4657 1.0000
6.500 1.0764 0.02031 0.01101 -0.0730 0.4567 1.0000
6.750 1.0917 0.02068 0.01146 -0.0708 0.4464 1.0000
7.000 1.1111 0.02102 0.01176 -0.0692 0.4370 1.0000
7.250 1.1257 0.02140 0.01222 -0.0669 0.4264 1.0000
7.500 1.1423 0.02176 0.01259 -0.0649 0.4166 1.0000
7.750 1.1562 0.02214 0.01299 -0.0624 0.4055 1.0000
8.000 1.1675 0.02254 0.01344 -0.0596 0.3942 1.0000
8.250 1.1775 0.02294 0.01385 -0.0565 0.3818 1.0000
8.500 1.1854 0.02340 0.01428 -0.0532 0.3677 1.0000
8.750 1.1915 0.02395 0.01484 -0.0498 0.3518 1.0000
9.000 1.1974 0.02458 0.01545 -0.0466 0.3348 1.0000
9.250 1.2030 0.02532 0.01616 -0.0435 0.3164 1.0000
9.500 1.2082 0.02617 0.01698 -0.0405 0.2977 1.0000
9.750 1.2133 0.02712 0.01787 -0.0378 0.2804 1.0000
10.000 1.2177 0.02821 0.01889 -0.0351 0.2642 1.0000
10.250 1.2216 0.02941 0.02003 -0.0326 0.2491 1.0000
10.500 1.2250 0.03072 0.02128 -0.0302 0.2356 1.0000
10.750 1.2289 0.03210 0.02264 -0.0280 0.2232 1.0000
11.000 1.2331 0.03353 0.02406 -0.0261 0.2116 1.0000
11.250 1.2364 0.03510 0.02560 -0.0242 0.2012 1.0000
11.500 1.2395 0.03673 0.02722 -0.0224 0.1916 1.0000
11.750 1.2438 0.03835 0.02888 -0.0209 0.1825 1.0000
12.000 1.2454 0.04021 0.03072 -0.0193 0.1746 1.0000
12.250 1.2501 0.04193 0.03251 -0.0180 0.1663 1.0000
12.500 1.2508 0.04397 0.03451 -0.0167 0.1594 1.0000
12.750 1.2552 0.04582 0.03646 -0.0156 0.1521 1.0000
13.000 1.2562 0.04797 0.03860 -0.0145 0.1461 1.0000
13.250 1.2601 0.04997 0.04068 -0.0137 0.1400 1.0000
13.500 1.2618 0.05220 0.04296 -0.0128 0.1345 1.0000
13.750 1.2642 0.05442 0.04519 -0.0121 0.1298 1.0000
14.000 1.2675 0.05665 0.04751 -0.0115 0.1245 1.0000
14.250 1.2694 0.05904 0.04991 -0.0110 0.1205 1.0000
14.500 1.2725 0.06134 0.05225 -0.0106 0.1165 1.0000
14.750 1.2761 0.06369 0.05471 -0.0103 0.1125 1.0000
15.000 1.2793 0.06609 0.05715 -0.0100 0.1092 1.0000
15.250 1.2838 0.06830 0.05931 -0.0097 0.1065 1.0000
15.500 1.2881 0.07074 0.06191 -0.0096 0.1035 1.0000
15.750 1.2917 0.07324 0.06451 -0.0096 0.1007 1.0000
16.000 1.2952 0.07576 0.06711 -0.0096 0.0982 1.0000
16.250 1.3001 0.07807 0.06942 -0.0096 0.0961 1.0000
16.500 1.3048 0.08052 0.07194 -0.0096 0.0940 1.0000
16.750 1.3066 0.08344 0.07504 -0.0100 0.0920 1.0000
17.000 1.3086 0.08634 0.07806 -0.0104 0.0901 1.0000
17.250 1.3110 0.08919 0.08101 -0.0108 0.0883 1.0000
17.500 1.3146 0.09181 0.08369 -0.0112 0.0867 1.0000
17.750 1.3225 0.09376 0.08563 -0.0113 0.0852 1.0000
18.000 1.3181 0.09778 0.08985 -0.0125 0.0838 1.0000
18.250 1.3112 0.10226 0.09455 -0.0140 0.0823 1.0000
18.500 1.3045 0.10676 0.09924 -0.0156 0.0810 1.0000
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