GOE 477 AIRFOIL (goe477-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 477 AIRFOIL (goe477-il) Reynolds number: 1,000,000 Max Cl/Cd: 104.88 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe477-il-1000000-n5.txt Download as CSV file: xf-goe477-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.3542 0.07701 0.07439 -0.0876 0.8150 0.0063
-11.500 -0.3650 0.07203 0.06937 -0.0902 0.8124 0.0063
-11.250 -0.6192 0.02712 0.02367 -0.1155 0.8030 0.0053
-11.000 -0.6095 0.02375 0.02001 -0.1155 0.8011 0.0054
-10.750 -0.5933 0.02176 0.01782 -0.1152 0.7993 0.0055
-10.500 -0.5740 0.02035 0.01624 -0.1148 0.7978 0.0057
-10.250 -0.5533 0.01913 0.01486 -0.1144 0.7964 0.0058
-10.000 -0.5312 0.01816 0.01375 -0.1140 0.7950 0.0060
-9.750 -0.5084 0.01725 0.01268 -0.1137 0.7938 0.0062
-9.500 -0.4850 0.01642 0.01172 -0.1133 0.7926 0.0064
-9.250 -0.4608 0.01570 0.01089 -0.1130 0.7913 0.0066
-9.000 -0.4362 0.01505 0.01012 -0.1127 0.7900 0.0068
-8.750 -0.4115 0.01440 0.00937 -0.1124 0.7885 0.0070
-8.500 -0.3867 0.01373 0.00861 -0.1120 0.7869 0.0074
-8.250 -0.3613 0.01321 0.00800 -0.1118 0.7851 0.0077
-8.000 -0.3355 0.01274 0.00744 -0.1115 0.7833 0.0081
-7.750 -0.3094 0.01232 0.00692 -0.1113 0.7817 0.0085
-7.500 -0.2831 0.01194 0.00645 -0.1110 0.7802 0.0088
-7.250 -0.2567 0.01152 0.00596 -0.1108 0.7788 0.0093
-7.000 -0.2302 0.01111 0.00549 -0.1106 0.7776 0.0100
-6.750 -0.2034 0.01077 0.00511 -0.1104 0.7763 0.0107
-6.500 -0.1763 0.01048 0.00477 -0.1103 0.7750 0.0114
-6.250 -0.1494 0.01016 0.00440 -0.1101 0.7735 0.0124
-6.000 -0.1224 0.00985 0.00407 -0.1100 0.7719 0.0136
-5.750 -0.0951 0.00961 0.00378 -0.1098 0.7703 0.0147
-5.500 -0.0680 0.00933 0.00347 -0.1097 0.7683 0.0166
-5.250 -0.0409 0.00910 0.00320 -0.1095 0.7659 0.0189
-5.000 -0.0138 0.00886 0.00296 -0.1093 0.7633 0.0230
-4.750 0.0136 0.00865 0.00278 -0.1092 0.7609 0.0287
-4.500 0.0413 0.00849 0.00266 -0.1091 0.7583 0.0346
-4.250 0.0691 0.00839 0.00259 -0.1091 0.7556 0.0412
-4.000 0.0971 0.00832 0.00250 -0.1090 0.7529 0.0448
-3.750 0.1250 0.00828 0.00242 -0.1089 0.7500 0.0470
-3.500 0.1530 0.00822 0.00235 -0.1089 0.7455 0.0481
-3.250 0.1809 0.00817 0.00228 -0.1088 0.7400 0.0486
-3.000 0.2082 0.00806 0.00212 -0.1086 0.7344 0.0496
-2.750 0.2356 0.00787 0.00192 -0.1085 0.7280 0.0521
-2.500 0.2628 0.00776 0.00177 -0.1083 0.7206 0.0537
-2.250 0.2903 0.00765 0.00164 -0.1081 0.7126 0.0544
-2.000 0.3174 0.00756 0.00151 -0.1079 0.7030 0.0550
-1.750 0.3445 0.00749 0.00139 -0.1076 0.6913 0.0557
-1.500 0.3714 0.00745 0.00130 -0.1074 0.6781 0.0566
-1.250 0.3976 0.00745 0.00122 -0.1070 0.6610 0.0579
-1.000 0.4233 0.00748 0.00117 -0.1065 0.6402 0.0592
-0.750 0.4485 0.00757 0.00114 -0.1059 0.6153 0.0604
-0.500 0.4732 0.00771 0.00115 -0.1053 0.5868 0.0615
-0.250 0.4969 0.00788 0.00119 -0.1044 0.5499 0.0665
0.000 0.5179 0.00824 0.00130 -0.1031 0.4861 0.0710
0.500 0.5643 0.00867 0.00150 -0.1015 0.4169 0.0984
0.750 0.5890 0.00873 0.00158 -0.1009 0.3998 0.1331
1.000 0.6141 0.00878 0.00166 -0.1005 0.3854 0.1663
1.250 0.6393 0.00885 0.00174 -0.1000 0.3721 0.1933
1.500 0.6644 0.00893 0.00183 -0.0995 0.3589 0.2206
1.750 0.6890 0.00894 0.00193 -0.0990 0.3454 0.2787
2.000 0.7124 0.00883 0.00206 -0.0983 0.3311 0.4015
2.500 0.7899 0.00803 0.00248 -0.1039 0.2963 1.0000
2.750 0.8132 0.00820 0.00259 -0.1030 0.2845 1.0000
3.000 0.8365 0.00838 0.00271 -0.1022 0.2743 1.0000
3.250 0.8597 0.00857 0.00284 -0.1013 0.2647 1.0000
3.500 0.8833 0.00874 0.00297 -0.1005 0.2565 1.0000
3.750 0.9067 0.00892 0.00311 -0.0997 0.2495 1.0000
4.000 0.9305 0.00909 0.00325 -0.0989 0.2432 1.0000
4.250 0.9537 0.00928 0.00340 -0.0981 0.2373 1.0000
4.500 0.9777 0.00943 0.00355 -0.0974 0.2332 1.0000
4.750 1.0014 0.00960 0.00371 -0.0967 0.2289 1.0000
5.000 1.0247 0.00979 0.00388 -0.0959 0.2247 1.0000
5.250 1.0477 0.00999 0.00406 -0.0950 0.2186 1.0000
5.500 1.0701 0.01022 0.00426 -0.0941 0.2111 1.0000
5.750 1.0924 0.01044 0.00446 -0.0932 0.2036 1.0000
6.000 1.1144 0.01068 0.00467 -0.0922 0.1962 1.0000
6.250 1.1363 0.01091 0.00489 -0.0912 0.1897 1.0000
6.500 1.1579 0.01116 0.00511 -0.0902 0.1811 1.0000
6.750 1.1783 0.01145 0.00536 -0.0890 0.1702 1.0000
7.000 1.1970 0.01183 0.00566 -0.0875 0.1551 1.0000
7.250 1.1998 0.01287 0.00635 -0.0832 0.0988 1.0000
7.500 1.1964 0.01433 0.00747 -0.0780 0.0319 1.0000
7.750 1.2127 0.01479 0.00790 -0.0761 0.0232 1.0000
8.000 1.2295 0.01523 0.00834 -0.0745 0.0192 1.0000
8.250 1.2466 0.01568 0.00879 -0.0728 0.0163 1.0000
8.500 1.2635 0.01613 0.00925 -0.0713 0.0140 1.0000
8.750 1.2803 0.01661 0.00973 -0.0698 0.0126 1.0000
9.000 1.2970 0.01710 0.01025 -0.0682 0.0112 1.0000
9.250 1.3134 0.01762 0.01079 -0.0668 0.0101 1.0000
9.500 1.3290 0.01820 0.01139 -0.0652 0.0093 1.0000
9.750 1.3452 0.01875 0.01198 -0.0638 0.0086 1.0000
10.000 1.3607 0.01936 0.01262 -0.0623 0.0080 1.0000
10.250 1.3753 0.02003 0.01333 -0.0609 0.0074 1.0000
10.500 1.3894 0.02076 0.01409 -0.0593 0.0070 1.0000
10.750 1.4039 0.02146 0.01485 -0.0579 0.0066 1.0000
11.000 1.4174 0.02225 0.01568 -0.0565 0.0063 1.0000
11.250 1.4303 0.02309 0.01656 -0.0550 0.0059 1.0000
11.500 1.4422 0.02402 0.01753 -0.0536 0.0056 1.0000
11.750 1.4531 0.02503 0.01860 -0.0520 0.0053 1.0000
12.000 1.4648 0.02600 0.01965 -0.0506 0.0050 1.0000
12.250 1.4744 0.02715 0.02086 -0.0491 0.0049 1.0000
12.500 1.4853 0.02820 0.02196 -0.0478 0.0046 1.0000
12.750 1.4939 0.02946 0.02328 -0.0463 0.0044 1.0000
13.000 1.5014 0.03082 0.02471 -0.0449 0.0043 1.0000
13.250 1.5081 0.03226 0.02622 -0.0434 0.0042 1.0000
13.500 1.5130 0.03390 0.02792 -0.0420 0.0040 1.0000
13.750 1.5148 0.03585 0.02995 -0.0404 0.0039 1.0000
14.000 1.5182 0.03770 0.03189 -0.0392 0.0039 1.0000
14.250 1.5213 0.03967 0.03395 -0.0380 0.0038 1.0000
14.500 1.5215 0.04200 0.03638 -0.0369 0.0037 1.0000
14.750 1.5242 0.04417 0.03863 -0.0361 0.0036 1.0000
15.000 1.5245 0.04669 0.04124 -0.0353 0.0035 1.0000
15.250 1.5204 0.04984 0.04453 -0.0347 0.0035 1.0000
15.500 1.5202 0.05268 0.04745 -0.0345 0.0033 1.0000
15.750 1.5166 0.05604 0.05092 -0.0344 0.0033 1.0000
16.000 1.5121 0.05966 0.05464 -0.0345 0.0033 1.0000
16.250 1.5051 0.06379 0.05888 -0.0350 0.0032 1.0000
16.500 1.4974 0.06819 0.06339 -0.0357 0.0032 1.0000
16.750 1.4893 0.07278 0.06810 -0.0368 0.0031 1.0000
17.000 1.4807 0.07765 0.07307 -0.0381 0.0031 1.0000
17.250 1.4664 0.08362 0.07918 -0.0399 0.0031 1.0000
17.500 1.4557 0.08914 0.08480 -0.0418 0.0030 1.0000
17.750 1.4425 0.09510 0.09088 -0.0440 0.0030 1.0000
18.000 1.4294 0.10115 0.09704 -0.0462 0.0030 1.0000
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