GOE 458 AIRFOIL (goe458-il) Xfoil prediction polar at RE=200,000 Ncrit=5
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Airfoil: GOE 458 AIRFOIL (goe458-il) Reynolds number: 200,000 Max Cl/Cd: 86.94 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe458-il-200000-n5.txt Download as CSV file: xf-goe458-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 458 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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.2910 0.11101 0.10764 -0.0356 1.0000 0.0149
-8.750 -0.2944 0.10906 0.10576 -0.0348 1.0000 0.0149
-8.500 -0.2987 0.10729 0.10404 -0.0334 1.0000 0.0149
-8.250 -0.2811 0.10296 0.09972 -0.0386 0.9958 0.0150
-8.000 -0.2649 0.09888 0.09564 -0.0431 0.9908 0.0150
-7.750 -0.2484 0.09482 0.09158 -0.0477 0.9860 0.0150
-7.500 -0.2336 0.09091 0.08768 -0.0517 0.9796 0.0150
-7.250 -0.2190 0.08712 0.08390 -0.0558 0.9726 0.0151
-7.000 -0.1998 0.08289 0.07967 -0.0612 0.9670 0.0151
-6.750 -0.1822 0.07879 0.07557 -0.0660 0.9593 0.0151
-6.500 -0.1578 0.07413 0.07090 -0.0726 0.9548 0.0151
-6.250 -0.1378 0.06998 0.06673 -0.0778 0.9468 0.0150
-6.000 -0.1117 0.06539 0.06210 -0.0843 0.9419 0.0150
-5.750 -0.0933 0.06130 0.05796 -0.0880 0.9340 0.0146
-5.500 -0.0687 0.05694 0.05356 -0.0934 0.9286 0.0129
-5.250 -0.0431 0.05247 0.04901 -0.0992 0.9200 0.0119
-5.000 -0.0092 0.04721 0.04363 -0.1067 0.9142 0.0112
-4.750 0.0198 0.04241 0.03869 -0.1121 0.9055 0.0105
-4.500 0.0545 0.03676 0.03281 -0.1181 0.8991 0.0100
-4.250 0.0871 0.03056 0.02627 -0.1225 0.8913 0.0097
-4.000 0.1190 0.02509 0.02022 -0.1254 0.8850 0.0094
-3.750 0.1477 0.02159 0.01611 -0.1263 0.8777 0.0097
-3.500 0.1768 0.01906 0.01299 -0.1267 0.8712 0.0108
-3.250 0.2060 0.01829 0.01172 -0.1266 0.8640 0.0148
-3.000 0.2328 0.01640 0.00951 -0.1267 0.8568 0.0180
-2.750 0.2615 0.01507 0.00784 -0.1264 0.8497 0.0180
-2.500 0.2885 0.01406 0.00657 -0.1260 0.8417 0.0183
-2.250 0.3168 0.01322 0.00558 -0.1258 0.8348 0.0195
-2.000 0.3432 0.01266 0.00488 -0.1254 0.8257 0.0215
-1.750 0.3705 0.01212 0.00419 -0.1252 0.8174 0.0257
-1.500 0.3981 0.01184 0.00377 -0.1250 0.8089 0.0304
-1.250 0.4249 0.01164 0.00343 -0.1246 0.7995 0.0308
-1.000 0.4522 0.01148 0.00315 -0.1244 0.7905 0.0315
-0.750 0.4795 0.01134 0.00282 -0.1241 0.7811 0.0343
-0.500 0.5055 0.01100 0.00270 -0.1238 0.7707 0.1170
-0.250 0.5323 0.01097 0.00260 -0.1235 0.7607 0.1298
0.000 0.5592 0.01095 0.00252 -0.1232 0.7509 0.1462
0.250 0.5855 0.01083 0.00251 -0.1230 0.7404 0.1928
0.500 0.6117 0.01080 0.00251 -0.1227 0.7295 0.2195
0.750 0.6380 0.01076 0.00253 -0.1224 0.7193 0.2581
1.000 0.6641 0.01068 0.00256 -0.1221 0.7091 0.3170
1.250 0.6886 0.01030 0.00264 -0.1216 0.6976 0.4991
1.500 0.7238 0.00949 0.00265 -0.1230 0.6838 1.0000
1.750 0.7492 0.00963 0.00270 -0.1224 0.6696 1.0000
2.000 0.7746 0.00979 0.00280 -0.1219 0.6563 1.0000
2.250 0.7999 0.00995 0.00289 -0.1214 0.6438 1.0000
2.500 0.8252 0.01012 0.00299 -0.1209 0.6312 1.0000
2.750 0.8501 0.01030 0.00312 -0.1203 0.6177 1.0000
3.000 0.8748 0.01049 0.00326 -0.1197 0.6037 1.0000
3.250 0.8999 0.01068 0.00344 -0.1192 0.5921 1.0000
3.500 0.9253 0.01086 0.00374 -0.1187 0.5831 1.0000
3.750 0.9504 0.01106 0.00395 -0.1182 0.5735 1.0000
4.000 0.9754 0.01124 0.00420 -0.1177 0.5625 1.0000
4.250 0.9981 0.01148 0.00444 -0.1167 0.5395 1.0000
4.500 1.0131 0.01199 0.00462 -0.1141 0.4655 1.0000
4.750 1.0136 0.01368 0.00527 -0.1094 0.2882 1.0000
5.000 1.0098 0.01626 0.00660 -0.1048 0.0928 1.0000
5.250 1.0184 0.01793 0.00790 -0.1016 0.0107 1.0000
5.500 1.0372 0.01865 0.00870 -0.1001 0.0062 1.0000
5.750 1.0559 0.01938 0.00961 -0.0985 0.0056 1.0000
6.000 1.0733 0.02022 0.01063 -0.0966 0.0052 1.0000
6.250 1.0885 0.02118 0.01178 -0.0945 0.0050 1.0000
6.500 1.1007 0.02229 0.01304 -0.0919 0.0049 1.0000
6.750 1.1091 0.02351 0.01437 -0.0888 0.0048 1.0000
7.000 1.1156 0.02486 0.01602 -0.0854 0.0048 1.0000
7.250 1.1236 0.02628 0.01752 -0.0823 0.0048 1.0000
7.500 1.1336 0.02783 0.01915 -0.0796 0.0048 1.0000
7.750 1.1474 0.02946 0.02086 -0.0776 0.0049 1.0000
8.000 1.1668 0.03135 0.02283 -0.0762 0.0049 1.0000
8.250 1.1923 0.03348 0.02509 -0.0757 0.0051 1.0000
8.500 1.2212 0.03594 0.02774 -0.0758 0.0053 1.0000
8.750 1.2477 0.03861 0.03065 -0.0757 0.0055 1.0000
9.000 1.2685 0.04139 0.03368 -0.0747 0.0057 1.0000
9.250 1.2841 0.04430 0.03685 -0.0732 0.0060 1.0000
9.500 1.2960 0.04750 0.04030 -0.0714 0.0062 1.0000
16.250 1.0625 0.19873 0.19557 -0.1077 0.0161 1.0000
16.500 1.0659 0.20504 0.20187 -0.1111 0.0160 1.0000
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Polar data table (+)
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