GOE 57 AIRFOIL (goe57-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 57 AIRFOIL (goe57-il) Reynolds number: 1,000,000 Max Cl/Cd: 102.2 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe57-il-1000000-n5.txt Download as CSV file: xf-goe57-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 57 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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.3531 0.10281 0.10121 -0.0242 1.0000 0.0060
-9.250 -0.3574 0.09767 0.09608 -0.0258 1.0000 0.0067
-9.000 -0.3591 0.09391 0.09235 -0.0267 1.0000 0.0070
-8.750 -0.3559 0.09173 0.09019 -0.0267 1.0000 0.0072
-8.250 -0.3212 0.08516 0.08362 -0.0350 0.9873 0.0078
-8.000 -0.3045 0.08104 0.07949 -0.0403 0.9725 0.0085
-7.750 -0.2851 0.07372 0.07213 -0.0508 0.9482 0.0098
-7.500 -0.2638 0.07091 0.06924 -0.0551 0.9240 0.0101
-7.250 -0.2449 0.06833 0.06657 -0.0585 0.9056 0.0104
-7.000 -0.2251 0.06534 0.06349 -0.0625 0.8918 0.0110
-6.750 -0.2005 0.05644 0.05447 -0.0750 0.8795 0.0135
-6.500 -0.1764 0.05460 0.05257 -0.0778 0.8711 0.0138
-6.250 -0.1517 0.05257 0.05046 -0.0807 0.8628 0.0141
-6.000 -0.1257 0.05008 0.04790 -0.0842 0.8530 0.0147
-5.750 -0.0862 0.04086 0.03844 -0.0964 0.8452 0.0181
-5.500 -0.0559 0.03687 0.03429 -0.1010 0.8352 0.0188
-5.250 -0.0294 0.03567 0.03301 -0.1023 0.8251 0.0191
-5.000 -0.0023 0.03417 0.03140 -0.1037 0.8140 0.0195
-4.750 0.0251 0.03239 0.02948 -0.1053 0.7979 0.0200
-4.500 0.0530 0.03036 0.02727 -0.1069 0.7772 0.0207
-4.250 0.0819 0.02805 0.02476 -0.1085 0.7569 0.0218
-4.000 0.1127 0.02447 0.02087 -0.1106 0.7376 0.0228
-3.750 0.1455 0.01702 0.01276 -0.1135 0.7218 0.0237
-3.500 0.1730 0.01263 0.00767 -0.1144 0.6995 0.0246
-3.250 0.1995 0.01199 0.00675 -0.1142 0.6682 0.0249
-3.000 0.2262 0.01164 0.00617 -0.1140 0.6409 0.0251
-2.750 0.2533 0.01140 0.00577 -0.1139 0.6192 0.0253
-2.500 0.2803 0.01004 0.00404 -0.1140 0.5996 0.0265
-2.250 0.3073 0.00979 0.00364 -0.1138 0.5751 0.0271
-2.000 0.3342 0.00965 0.00334 -0.1136 0.5472 0.0275
-1.750 0.3611 0.00954 0.00308 -0.1134 0.5180 0.0278
-1.500 0.3874 0.00952 0.00285 -0.1131 0.4757 0.0281
-1.250 0.4134 0.00956 0.00266 -0.1127 0.4294 0.0283
-1.000 0.4397 0.00959 0.00248 -0.1125 0.3907 0.0285
-0.750 0.4663 0.00959 0.00233 -0.1122 0.3606 0.0287
-0.500 0.4931 0.00958 0.00219 -0.1120 0.3347 0.0289
-0.250 0.5199 0.00963 0.00211 -0.1118 0.3089 0.0293
0.000 0.5463 0.00975 0.00208 -0.1115 0.2765 0.0298
0.250 0.5727 0.00986 0.00203 -0.1113 0.2439 0.0301
0.500 0.5978 0.01017 0.00207 -0.1108 0.1871 0.0304
0.750 0.6249 0.01021 0.00204 -0.1106 0.1770 0.0308
1.000 0.6522 0.01024 0.00203 -0.1105 0.1714 0.0315
1.250 0.6795 0.01027 0.00204 -0.1104 0.1684 0.0326
1.500 0.7068 0.01032 0.00208 -0.1102 0.1658 0.0339
1.750 0.7340 0.01038 0.00212 -0.1100 0.1633 0.0363
2.000 0.7613 0.01043 0.00219 -0.1099 0.1610 0.0414
2.250 0.7884 0.01051 0.00227 -0.1097 0.1590 0.0454
2.500 0.8156 0.01057 0.00236 -0.1096 0.1582 0.0516
2.750 0.8428 0.01063 0.00245 -0.1094 0.1574 0.0592
3.250 0.8966 0.01079 0.00269 -0.1091 0.1505 0.1038
3.500 0.9236 0.01076 0.00289 -0.1091 0.1474 0.2358
3.750 0.9462 0.00957 0.00319 -0.1084 0.1440 1.0000
4.000 0.9733 0.00968 0.00329 -0.1083 0.1423 1.0000
4.250 1.0001 0.00982 0.00341 -0.1081 0.1389 1.0000
4.500 1.0261 0.01004 0.00356 -0.1078 0.1300 1.0000
4.750 1.0484 0.01075 0.00396 -0.1070 0.0731 1.0000
5.000 1.0696 0.01162 0.00457 -0.1059 0.0180 1.0000
5.250 1.0951 0.01190 0.00486 -0.1055 0.0136 1.0000
5.500 1.1204 0.01220 0.00517 -0.1051 0.0112 1.0000
5.750 1.1458 0.01247 0.00547 -0.1046 0.0103 1.0000
6.000 1.1710 0.01276 0.00577 -0.1042 0.0094 1.0000
6.250 1.1959 0.01308 0.00611 -0.1038 0.0084 1.0000
6.500 1.2201 0.01347 0.00652 -0.1032 0.0075 1.0000
6.750 1.2441 0.01388 0.00696 -0.1026 0.0070 1.0000
7.000 1.2683 0.01425 0.00736 -0.1020 0.0066 1.0000
7.250 1.2921 0.01465 0.00780 -0.1014 0.0062 1.0000
7.500 1.3157 0.01505 0.00822 -0.1007 0.0057 1.0000
7.750 1.3390 0.01546 0.00865 -0.1001 0.0053 1.0000
8.000 1.3604 0.01611 0.00934 -0.0991 0.0048 1.0000
8.250 1.3828 0.01659 0.00987 -0.0983 0.0047 1.0000
8.500 1.4046 0.01713 0.01046 -0.0974 0.0045 1.0000
8.750 1.4258 0.01771 0.01111 -0.0964 0.0042 1.0000
9.000 1.4462 0.01833 0.01179 -0.0954 0.0040 1.0000
9.250 1.4662 0.01896 0.01248 -0.0942 0.0039 1.0000
9.500 1.4855 0.01961 0.01318 -0.0930 0.0037 1.0000
9.750 1.5043 0.02026 0.01389 -0.0918 0.0036 1.0000
10.000 1.5222 0.02096 0.01464 -0.0904 0.0034 1.0000
10.250 1.5379 0.02179 0.01553 -0.0887 0.0033 1.0000
10.500 1.5467 0.02311 0.01697 -0.0861 0.0031 1.0000
10.750 1.5591 0.02390 0.01784 -0.0838 0.0030 1.0000
11.000 1.5691 0.02476 0.01879 -0.0813 0.0030 1.0000
11.250 1.5774 0.02576 0.01988 -0.0786 0.0029 1.0000
11.500 1.5833 0.02695 0.02117 -0.0758 0.0028 1.0000
11.750 1.5874 0.02833 0.02265 -0.0730 0.0027 1.0000
12.000 1.5903 0.02989 0.02433 -0.0705 0.0027 1.0000
12.250 1.5919 0.03167 0.02622 -0.0681 0.0026 1.0000
12.500 1.5929 0.03364 0.02830 -0.0660 0.0025 1.0000
12.750 1.5926 0.03584 0.03061 -0.0641 0.0025 1.0000
13.000 1.5918 0.03825 0.03313 -0.0626 0.0024 1.0000
13.250 1.5895 0.04093 0.03593 -0.0613 0.0024 1.0000
13.500 1.5873 0.04377 0.03891 -0.0604 0.0024 1.0000
13.750 1.5820 0.04713 0.04239 -0.0597 0.0023 1.0000
14.000 1.5772 0.05062 0.04601 -0.0595 0.0023 1.0000
14.250 1.5715 0.05444 0.04994 -0.0596 0.0023 1.0000
14.500 1.5640 0.05866 0.05429 -0.0601 0.0022 1.0000
14.750 1.5568 0.06304 0.05879 -0.0609 0.0022 1.0000
15.000 1.5470 0.06799 0.06386 -0.0620 0.0022 1.0000
15.250 1.5355 0.07332 0.06933 -0.0634 0.0022 1.0000
15.500 1.5243 0.07883 0.07496 -0.0651 0.0022 1.0000
15.750 1.5113 0.08477 0.08103 -0.0670 0.0022 1.0000
16.000 1.5008 0.09046 0.08683 -0.0691 0.0021 1.0000
16.250 1.4871 0.09671 0.09320 -0.0713 0.0021 1.0000
16.500 1.4740 0.10298 0.09959 -0.0737 0.0021 1.0000
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