GOE 477 AIRFOIL (goe477-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 477 AIRFOIL (goe477-il) Reynolds number: 200,000 Max Cl/Cd: 75.05 at α=2.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe477-il-200000-n5.txt Download as CSV file: xf-goe477-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 477 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.1832 0.08795 0.08427 -0.0775 0.9216 0.0173
-9.250 -0.1757 0.08284 0.07914 -0.0823 0.9134 0.0182
-9.000 -0.1683 0.07838 0.07466 -0.0861 0.9060 0.0182
-8.750 -0.1643 0.07394 0.07021 -0.0895 0.8991 0.0183
-8.500 -0.1635 0.06969 0.06595 -0.0925 0.8919 0.0183
-8.250 -0.1683 0.06544 0.06170 -0.0950 0.8847 0.0183
-8.000 -0.1782 0.05999 0.05625 -0.0992 0.8775 0.0185
-7.750 -0.1863 0.05224 0.04842 -0.1060 0.8714 0.0185
-7.500 -0.2356 0.02766 0.02254 -0.1175 0.8617 0.0185
-7.250 -0.2207 0.02433 0.01864 -0.1173 0.8587 0.0196
-7.000 -0.1963 0.02387 0.01811 -0.1172 0.8563 0.0209
-6.750 -0.1750 0.02253 0.01651 -0.1167 0.8531 0.0222
-6.500 -0.1537 0.02082 0.01441 -0.1162 0.8499 0.0238
-6.250 -0.1309 0.01942 0.01267 -0.1156 0.8471 0.0258
-6.000 -0.1049 0.01915 0.01235 -0.1155 0.8446 0.0283
-5.750 -0.0789 0.01864 0.01167 -0.1152 0.8424 0.0312
-5.500 -0.0532 0.01793 0.01070 -0.1148 0.8402 0.0347
-5.250 -0.0281 0.01772 0.01047 -0.1145 0.8373 0.0387
-5.000 -0.0022 0.01745 0.01006 -0.1142 0.8344 0.0439
-4.750 0.0245 0.01716 0.00950 -0.1138 0.8319 0.0486
-4.500 0.0505 0.01679 0.00911 -0.1137 0.8296 0.0530
-4.250 0.0776 0.01658 0.00876 -0.1135 0.8274 0.0579
-4.000 0.1050 0.01637 0.00833 -0.1133 0.8253 0.0618
-3.750 0.1295 0.01595 0.00796 -0.1129 0.8222 0.0658
-3.500 0.1553 0.01572 0.00767 -0.1126 0.8192 0.0694
-3.250 0.1817 0.01548 0.00731 -0.1122 0.8156 0.0726
-3.000 0.2087 0.01512 0.00686 -0.1119 0.8120 0.0745
-2.750 0.2345 0.01472 0.00644 -0.1114 0.8079 0.0764
-2.500 0.2593 0.01446 0.00617 -0.1108 0.8030 0.0781
-2.250 0.2856 0.01424 0.00592 -0.1104 0.7990 0.0809
-2.000 0.3130 0.01402 0.00564 -0.1102 0.7956 0.0842
-1.750 0.3383 0.01386 0.00544 -0.1096 0.7910 0.0865
-1.500 0.3635 0.01362 0.00522 -0.1090 0.7855 0.0901
-1.250 0.3908 0.01336 0.00492 -0.1087 0.7803 0.0957
-1.000 0.4151 0.01315 0.00472 -0.1078 0.7715 0.1038
-0.750 0.4422 0.01282 0.00441 -0.1073 0.7641 0.1217
-0.500 0.4657 0.01258 0.00433 -0.1064 0.7548 0.1593
-0.250 0.4923 0.01231 0.00416 -0.1061 0.7489 0.2077
0.000 0.5160 0.01211 0.00415 -0.1053 0.7406 0.2592
0.250 0.5412 0.01174 0.00405 -0.1048 0.7347 0.3548
0.500 0.5568 0.01077 0.00416 -0.1024 0.7262 0.6863
1.000 0.6517 0.01021 0.00395 -0.1101 0.7058 1.0000
1.250 0.6755 0.01023 0.00392 -0.1091 0.6934 1.0000
1.500 0.6998 0.01023 0.00385 -0.1082 0.6795 1.0000
1.750 0.7242 0.01023 0.00375 -0.1073 0.6624 1.0000
2.000 0.7483 0.01025 0.00363 -0.1063 0.6402 1.0000
2.250 0.7713 0.01035 0.00354 -0.1051 0.6112 1.0000
2.500 0.7925 0.01056 0.00353 -0.1036 0.5733 1.0000
2.750 0.8107 0.01094 0.00361 -0.1016 0.5228 1.0000
3.000 0.8264 0.01145 0.00380 -0.0993 0.4738 1.0000
3.250 0.8433 0.01195 0.00407 -0.0973 0.4415 1.0000
3.500 0.8621 0.01238 0.00435 -0.0956 0.4185 1.0000
3.750 0.8816 0.01278 0.00463 -0.0942 0.3997 1.0000
4.000 0.9015 0.01315 0.00493 -0.0928 0.3831 1.0000
4.250 0.9218 0.01351 0.00522 -0.0915 0.3681 1.0000
4.500 0.9420 0.01387 0.00552 -0.0902 0.3538 1.0000
4.750 0.9619 0.01424 0.00584 -0.0889 0.3399 1.0000
5.000 0.9816 0.01462 0.00616 -0.0875 0.3269 1.0000
5.250 1.0013 0.01499 0.00649 -0.0862 0.3148 1.0000
5.500 1.0214 0.01535 0.00685 -0.0849 0.3047 1.0000
5.750 1.0404 0.01575 0.00721 -0.0835 0.2962 1.0000
6.000 1.0605 0.01610 0.00759 -0.0823 0.2883 1.0000
6.500 1.0983 0.01688 0.00840 -0.0794 0.2760 1.0000
6.750 1.1161 0.01729 0.00883 -0.0778 0.2700 1.0000
7.000 1.1334 0.01771 0.00926 -0.0761 0.2621 1.0000
7.500 1.1653 0.01865 0.01019 -0.0726 0.2405 1.0000
7.750 1.1820 0.01912 0.01069 -0.0710 0.2319 1.0000
8.000 1.1972 0.01967 0.01123 -0.0692 0.2223 1.0000
8.250 1.2137 0.02017 0.01178 -0.0677 0.2103 1.0000
8.500 1.2284 0.02077 0.01238 -0.0660 0.1943 1.0000
8.750 1.2415 0.02151 0.01304 -0.0642 0.1655 1.0000
9.000 1.2304 0.02414 0.01488 -0.0600 0.0563 1.0000
9.250 1.2359 0.02571 0.01638 -0.0575 0.0350 1.0000
9.500 1.2459 0.02693 0.01765 -0.0556 0.0288 1.0000
9.750 1.2566 0.02808 0.01894 -0.0538 0.0253 1.0000
10.000 1.2667 0.02926 0.02027 -0.0521 0.0231 1.0000
10.250 1.2743 0.03064 0.02177 -0.0502 0.0213 1.0000
10.500 1.2764 0.03246 0.02371 -0.0481 0.0197 1.0000
10.750 1.2831 0.03394 0.02534 -0.0464 0.0186 1.0000
11.000 1.2865 0.03571 0.02725 -0.0446 0.0178 1.0000
11.250 1.2884 0.03765 0.02934 -0.0429 0.0168 1.0000
11.500 1.2890 0.03976 0.03155 -0.0413 0.0161 1.0000
11.750 1.2870 0.04218 0.03407 -0.0398 0.0156 1.0000
12.000 1.2816 0.04504 0.03704 -0.0384 0.0150 1.0000
12.250 1.2805 0.04761 0.03974 -0.0373 0.0144 1.0000
12.500 1.2787 0.05038 0.04265 -0.0364 0.0140 1.0000
12.750 1.2756 0.05345 0.04584 -0.0358 0.0135 1.0000
13.000 1.2724 0.05665 0.04916 -0.0353 0.0132 1.0000
13.250 1.2694 0.05999 0.05261 -0.0351 0.0130 1.0000
13.500 1.2665 0.06344 0.05615 -0.0351 0.0127 1.0000
13.750 1.2639 0.06695 0.05976 -0.0353 0.0124 1.0000
14.000 1.2612 0.07056 0.06343 -0.0356 0.0121 1.0000
14.250 1.2589 0.07414 0.06707 -0.0359 0.0118 1.0000
14.500 1.2596 0.07743 0.07054 -0.0361 0.0115 1.0000
14.750 1.2602 0.08081 0.07406 -0.0365 0.0110 1.0000
15.000 1.2611 0.08415 0.07753 -0.0370 0.0107 1.0000
15.250 1.2619 0.08756 0.08105 -0.0375 0.0103 1.0000
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Polar data table (+)
Polar graphs
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