GOE 300 (FRIEDRICHSHAFEN G20) AIRFOIL (goe300-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 300 (FRIEDRICHSHAFEN G20) AIRFOIL (goe300-il) Reynolds number: 1,000,000 Max Cl/Cd: 126.87 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe300-il-1000000-n5.txt Download as CSV file: xf-goe300-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 300 (FRIEDRICHSHAFEN G20) 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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.2337 0.09167 0.08962 -0.0411 0.8460 0.0068
-8.750 -0.2258 0.08889 0.08680 -0.0426 0.8335 0.0069
-8.250 -0.2485 0.06683 0.06462 -0.0645 0.8081 0.0088
-8.000 -0.2350 0.05485 0.05245 -0.0811 0.7963 0.0094
-7.750 -0.2121 0.04822 0.04563 -0.0897 0.7840 0.0098
-7.500 -0.1866 0.03997 0.03706 -0.0992 0.7721 0.0103
-7.250 -0.1606 0.03577 0.03263 -0.1032 0.7584 0.0107
-7.000 -0.1343 0.03265 0.02930 -0.1058 0.7432 0.0111
-6.750 -0.1080 0.02931 0.02575 -0.1082 0.7280 0.0116
-6.500 -0.0828 0.02310 0.01905 -0.1117 0.7149 0.0123
-6.250 -0.0593 0.01718 0.01249 -0.1137 0.7017 0.0130
-6.000 -0.0354 0.01337 0.00818 -0.1144 0.6877 0.0138
-5.750 -0.0096 0.01162 0.00617 -0.1146 0.6731 0.0149
-5.500 0.0177 0.01101 0.00541 -0.1145 0.6604 0.0160
-5.250 0.0453 0.01057 0.00483 -0.1144 0.6489 0.0171
-5.000 0.0727 0.01011 0.00425 -0.1143 0.6355 0.0189
-4.750 0.1004 0.00982 0.00385 -0.1142 0.6210 0.0209
-4.500 0.1280 0.00949 0.00344 -0.1141 0.6087 0.0243
-4.250 0.1558 0.00927 0.00316 -0.1140 0.5987 0.0285
-4.000 0.1838 0.00915 0.00299 -0.1139 0.5879 0.0325
-3.750 0.2120 0.00916 0.00299 -0.1138 0.5775 0.0368
-3.500 0.2401 0.00916 0.00291 -0.1137 0.5678 0.0393
-3.250 0.2683 0.00911 0.00280 -0.1136 0.5586 0.0406
-3.000 0.2966 0.00912 0.00279 -0.1135 0.5512 0.0428
-2.750 0.3250 0.00917 0.00282 -0.1134 0.5438 0.0445
-2.500 0.3532 0.00920 0.00281 -0.1133 0.5367 0.0460
-2.250 0.3816 0.00919 0.00276 -0.1133 0.5304 0.0475
-2.000 0.4098 0.00920 0.00272 -0.1132 0.5242 0.0487
-1.750 0.4380 0.00920 0.00267 -0.1131 0.5187 0.0494
-1.500 0.4663 0.00918 0.00262 -0.1131 0.5131 0.0499
-1.250 0.4942 0.00908 0.00246 -0.1130 0.5057 0.0504
-1.000 0.5220 0.00888 0.00220 -0.1129 0.4979 0.0519
-0.750 0.5499 0.00883 0.00211 -0.1128 0.4892 0.0530
-0.500 0.5780 0.00880 0.00206 -0.1128 0.4828 0.0541
-0.250 0.6059 0.00881 0.00203 -0.1127 0.4742 0.0552
0.000 0.6338 0.00880 0.00199 -0.1126 0.4648 0.0560
0.250 0.6614 0.00882 0.00195 -0.1125 0.4536 0.0567
0.500 0.6891 0.00884 0.00192 -0.1125 0.4416 0.0574
0.750 0.7167 0.00888 0.00190 -0.1124 0.4289 0.0581
1.000 0.7440 0.00895 0.00191 -0.1122 0.4137 0.0588
1.250 0.7711 0.00906 0.00193 -0.1121 0.3966 0.0594
1.500 0.7978 0.00921 0.00198 -0.1119 0.3775 0.0600
1.750 0.8248 0.00933 0.00204 -0.1117 0.3630 0.0606
2.000 0.8519 0.00943 0.00210 -0.1116 0.3529 0.0612
2.250 0.8789 0.00954 0.00216 -0.1115 0.3428 0.0641
2.500 0.9062 0.00963 0.00225 -0.1114 0.3346 0.0672
2.750 0.9331 0.00976 0.00235 -0.1112 0.3270 0.0700
3.000 0.9605 0.00983 0.00243 -0.1111 0.3227 0.0722
3.250 0.9878 0.00992 0.00252 -0.1111 0.3180 0.0761
3.500 1.0148 0.01003 0.00264 -0.1110 0.3132 0.0816
3.750 1.0419 0.01014 0.00275 -0.1109 0.3092 0.0859
4.000 1.0691 0.01021 0.00287 -0.1108 0.3058 0.0932
4.250 1.0961 0.01031 0.00298 -0.1107 0.3019 0.0996
4.500 1.1228 0.01045 0.00313 -0.1106 0.2968 0.1076
4.750 1.1494 0.01058 0.00327 -0.1104 0.2915 0.1157
5.000 1.1761 0.01069 0.00342 -0.1103 0.2858 0.1285
5.250 1.2024 0.01084 0.00359 -0.1102 0.2796 0.1523
5.750 1.2522 0.00987 0.00411 -0.1096 0.2689 1.0000
6.000 1.2778 0.01010 0.00429 -0.1093 0.2601 1.0000
6.250 1.3029 0.01038 0.00450 -0.1090 0.2472 1.0000
6.500 1.3260 0.01083 0.00480 -0.1084 0.2192 1.0000
6.750 1.3448 0.01165 0.00536 -0.1072 0.1772 1.0000
7.000 1.3685 0.01201 0.00568 -0.1067 0.1685 1.0000
7.250 1.3920 0.01237 0.00601 -0.1061 0.1614 1.0000
7.500 1.4165 0.01263 0.00628 -0.1057 0.1580 1.0000
7.750 1.4406 0.01291 0.00656 -0.1053 0.1547 1.0000
8.000 1.4637 0.01325 0.00690 -0.1047 0.1498 1.0000
8.250 1.4865 0.01362 0.00726 -0.1040 0.1435 1.0000
8.500 1.5098 0.01391 0.00756 -0.1035 0.1389 1.0000
8.750 1.5317 0.01430 0.00793 -0.1028 0.1327 1.0000
9.000 1.5537 0.01466 0.00830 -0.1020 0.1279 1.0000
9.250 1.5756 0.01500 0.00865 -0.1013 0.1220 1.0000
9.500 1.5952 0.01550 0.00910 -0.1002 0.1130 1.0000
9.750 1.6137 0.01603 0.00958 -0.0990 0.1027 1.0000
10.000 1.6292 0.01669 0.01017 -0.0974 0.0904 1.0000
10.250 1.6399 0.01749 0.01089 -0.0949 0.0773 1.0000
10.500 1.6469 0.01851 0.01183 -0.0920 0.0614 1.0000
10.750 1.6385 0.02053 0.01363 -0.0872 0.0284 1.0000
11.000 1.6445 0.02176 0.01486 -0.0847 0.0205 1.0000
11.250 1.6530 0.02288 0.01601 -0.0827 0.0169 1.0000
11.500 1.6620 0.02402 0.01718 -0.0808 0.0146 1.0000
11.750 1.6715 0.02517 0.01838 -0.0792 0.0129 1.0000
12.000 1.6802 0.02644 0.01968 -0.0776 0.0115 1.0000
12.250 1.6888 0.02775 0.02104 -0.0761 0.0104 1.0000
12.500 1.6957 0.02926 0.02261 -0.0747 0.0095 1.0000
12.750 1.7037 0.03074 0.02415 -0.0734 0.0088 1.0000
13.000 1.7102 0.03240 0.02588 -0.0722 0.0082 1.0000
13.250 1.7151 0.03427 0.02781 -0.0711 0.0077 1.0000
13.500 1.7193 0.03627 0.02989 -0.0701 0.0073 1.0000
13.750 1.7237 0.03831 0.03200 -0.0692 0.0070 1.0000
14.000 1.7268 0.04054 0.03430 -0.0684 0.0066 1.0000
14.250 1.7285 0.04299 0.03683 -0.0677 0.0063 1.0000
14.500 1.7285 0.04569 0.03960 -0.0671 0.0060 1.0000
14.750 1.7271 0.04861 0.04260 -0.0666 0.0057 1.0000
15.000 1.7272 0.05146 0.04555 -0.0663 0.0055 1.0000
15.250 1.7262 0.05451 0.04870 -0.0661 0.0053 1.0000
15.500 1.7238 0.05779 0.05207 -0.0660 0.0051 1.0000
15.750 1.7201 0.06128 0.05565 -0.0660 0.0050 1.0000
16.000 1.7153 0.06498 0.05944 -0.0661 0.0048 1.0000
16.250 1.7097 0.06887 0.06342 -0.0664 0.0047 1.0000
16.500 1.7026 0.07299 0.06763 -0.0667 0.0046 1.0000
16.750 1.6943 0.07734 0.07208 -0.0672 0.0045 1.0000
17.000 1.6848 0.08196 0.07680 -0.0679 0.0043 1.0000
17.250 1.6758 0.08657 0.08152 -0.0687 0.0043 1.0000
17.500 1.6666 0.09125 0.08630 -0.0695 0.0042 1.0000
17.750 1.6569 0.09606 0.09122 -0.0705 0.0041 1.0000
18.000 1.6469 0.10103 0.09629 -0.0717 0.0041 1.0000
18.250 1.6362 0.10616 0.10154 -0.0730 0.0040 1.0000
18.500 1.6253 0.11136 0.10684 -0.0745 0.0039 1.0000
18.750 1.6143 0.11664 0.11222 -0.0761 0.0039 1.0000
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Polar data table (+)
Polar graphs
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