XFOIL Version 6.96 Calculated polar for: GOE 528 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 = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -11.500 -0.2231 0.11465 0.11299 -0.0498 0.9969 0.0176 -11.250 -0.2068 0.11198 0.11032 -0.0518 0.9905 0.0179 -11.000 -0.1945 0.10885 0.10719 -0.0541 0.9794 0.0180 -10.750 -0.1776 0.10522 0.10355 -0.0580 0.9660 0.0182 -10.500 -0.1531 0.10138 0.09968 -0.0637 0.9544 0.0191 -10.250 -0.1381 0.09225 0.09049 -0.0763 0.9421 0.0207 -10.000 -0.1076 0.08637 0.08455 -0.0854 0.9321 0.0210 -9.750 -0.0661 0.08321 0.08131 -0.0931 0.9213 0.0213 -9.500 -0.0291 0.07979 0.07777 -0.1010 0.9035 0.0221 -9.250 -0.0100 0.07649 0.07434 -0.1057 0.8811 0.0227 -9.000 -0.0229 0.06963 0.06738 -0.1112 0.8571 0.0244 -8.750 -0.0011 0.05416 0.05183 -0.1008 0.8048 0.0248 -8.250 0.0109 0.05014 0.04776 -0.1008 0.7861 0.0251 -8.000 -0.0272 0.05934 0.05692 -0.1120 0.8028 0.0251 -7.750 -0.0245 0.05678 0.05432 -0.1134 0.7923 0.0253 -7.500 -0.0167 0.05455 0.05206 -0.1147 0.7823 0.0256 -7.250 -0.0098 0.05155 0.04901 -0.1170 0.7732 0.0261 -7.000 -0.0028 0.04769 0.04507 -0.1200 0.7636 0.0270 -6.500 -0.0418 0.01929 0.01508 -0.1270 0.7486 0.0266 -6.250 -0.0230 0.01724 0.01266 -0.1260 0.7412 0.0270 -6.000 -0.0009 0.01594 0.01110 -0.1251 0.7333 0.0276 -5.750 0.0230 0.01514 0.01007 -0.1244 0.7258 0.0281 -5.500 0.0482 0.01461 0.00936 -0.1238 0.7172 0.0285 -5.250 0.0721 0.01370 0.00822 -0.1231 0.7090 0.0288 -5.000 0.0956 0.01243 0.00680 -0.1224 0.7001 0.0293 -4.750 0.1210 0.01190 0.00619 -0.1219 0.6913 0.0297 -4.500 0.1468 0.01154 0.00576 -0.1214 0.6811 0.0302 -4.250 0.1731 0.01130 0.00546 -0.1210 0.6712 0.0308 -4.000 0.1989 0.01100 0.00508 -0.1204 0.6605 0.0314 -3.750 0.2249 0.01066 0.00465 -0.1199 0.6490 0.0317 -3.500 0.2509 0.01037 0.00428 -0.1194 0.6373 0.0322 -3.250 0.2767 0.01012 0.00395 -0.1188 0.6253 0.0326 -3.000 0.3024 0.00992 0.00366 -0.1182 0.6128 0.0330 -2.750 0.3287 0.00976 0.00344 -0.1177 0.6006 0.0333 -2.500 0.3542 0.00948 0.00309 -0.1171 0.5895 0.0338 -2.250 0.3792 0.00920 0.00275 -0.1165 0.5787 0.0349 -2.000 0.4055 0.00908 0.00259 -0.1160 0.5687 0.0357 -1.750 0.4317 0.00899 0.00245 -0.1156 0.5600 0.0364 -1.500 0.4580 0.00891 0.00233 -0.1151 0.5514 0.0373 -1.250 0.4845 0.00885 0.00222 -0.1147 0.5441 0.0381 -1.000 0.5112 0.00880 0.00213 -0.1143 0.5370 0.0389 -0.750 0.5372 0.00871 0.00200 -0.1138 0.5302 0.0406 -0.500 0.5642 0.00864 0.00193 -0.1135 0.5241 0.0428 -0.250 0.5907 0.00864 0.00189 -0.1131 0.5180 0.0452 0.000 0.6172 0.00859 0.00185 -0.1128 0.5124 0.0509 0.250 0.6437 0.00847 0.00184 -0.1124 0.5069 0.0854 0.500 0.6688 0.00828 0.00186 -0.1119 0.5013 0.1749 0.750 0.6939 0.00808 0.00192 -0.1114 0.4962 0.2840 1.000 0.7193 0.00788 0.00199 -0.1110 0.4911 0.3937 1.250 0.7428 0.00763 0.00208 -0.1102 0.4858 0.5375 1.500 0.8124 0.00684 0.00229 -0.1195 0.4790 1.0000 1.750 0.8375 0.00692 0.00233 -0.1188 0.4735 1.0000 2.000 0.8618 0.00704 0.00239 -0.1180 0.4677 1.0000 2.250 0.8869 0.00712 0.00244 -0.1174 0.4625 1.0000 2.500 0.9120 0.00721 0.00249 -0.1167 0.4564 1.0000 2.750 0.9359 0.00735 0.00257 -0.1159 0.4501 1.0000 3.000 0.9613 0.00743 0.00263 -0.1153 0.4449 1.0000 3.250 0.9861 0.00754 0.00271 -0.1147 0.4392 1.0000 3.500 1.0100 0.00769 0.00280 -0.1138 0.4333 1.0000 3.750 1.0356 0.00776 0.00288 -0.1133 0.4285 1.0000 4.000 1.0602 0.00788 0.00297 -0.1127 0.4226 1.0000 4.250 1.0842 0.00804 0.00309 -0.1119 0.4166 1.0000 4.500 1.1093 0.00814 0.00318 -0.1113 0.4104 1.0000 4.750 1.1330 0.00830 0.00330 -0.1106 0.4037 1.0000 5.000 1.1576 0.00843 0.00342 -0.1099 0.3974 1.0000 5.250 1.1812 0.00859 0.00355 -0.1091 0.3895 1.0000 5.500 1.2049 0.00875 0.00369 -0.1084 0.3817 1.0000 5.750 1.2281 0.00894 0.00384 -0.1075 0.3736 1.0000 6.000 1.2515 0.00911 0.00400 -0.1068 0.3667 1.0000 6.250 1.2746 0.00929 0.00416 -0.1059 0.3593 1.0000 6.500 1.2971 0.00949 0.00434 -0.1050 0.3518 1.0000 6.750 1.3194 0.00970 0.00453 -0.1040 0.3434 1.0000 7.000 1.3414 0.00992 0.00473 -0.1030 0.3359 1.0000 7.250 1.3630 0.01014 0.00493 -0.1020 0.3281 1.0000 7.500 1.3842 0.01037 0.00515 -0.1008 0.3203 1.0000 7.750 1.4035 0.01067 0.00540 -0.0994 0.3101 1.0000 8.000 1.4232 0.01090 0.00563 -0.0980 0.3018 1.0000 8.250 1.4396 0.01122 0.00591 -0.0960 0.2927 1.0000 8.500 1.4578 0.01148 0.00617 -0.0943 0.2842 1.0000 8.750 1.4744 0.01180 0.00647 -0.0924 0.2762 1.0000 9.000 1.4916 0.01211 0.00677 -0.0906 0.2679 1.0000 9.250 1.5081 0.01246 0.00711 -0.0888 0.2597 1.0000 9.500 1.5220 0.01293 0.00752 -0.0866 0.2486 1.0000 9.750 1.5376 0.01333 0.00791 -0.0848 0.2384 1.0000 10.000 1.5519 0.01381 0.00836 -0.0828 0.2282 1.0000 10.250 1.5647 0.01436 0.00887 -0.0806 0.2188 1.0000 10.500 1.5785 0.01489 0.00939 -0.0787 0.2092 1.0000 10.750 1.5916 0.01547 0.00995 -0.0767 0.2006 1.0000 11.000 1.6020 0.01621 0.01065 -0.0745 0.1903 1.0000 11.250 1.6134 0.01693 0.01136 -0.0726 0.1802 1.0000 11.500 1.6231 0.01778 0.01218 -0.0705 0.1691 1.0000 11.750 1.6311 0.01878 0.01314 -0.0684 0.1574 1.0000 12.000 1.6347 0.02010 0.01438 -0.0660 0.1406 1.0000 12.250 1.6275 0.02220 0.01631 -0.0627 0.1118 1.0000 12.500 1.6150 0.02487 0.01882 -0.0594 0.0868 1.0000 12.750 1.6169 0.02665 0.02060 -0.0576 0.0799 1.0000 13.000 1.6225 0.02822 0.02221 -0.0562 0.0754 1.0000 13.250 1.6257 0.03002 0.02404 -0.0548 0.0714 1.0000 13.500 1.6303 0.03178 0.02584 -0.0536 0.0677 1.0000 13.750 1.6373 0.03337 0.02749 -0.0527 0.0654 1.0000 14.000 1.6399 0.03539 0.02955 -0.0516 0.0619 1.0000 14.250 1.6410 0.03762 0.03182 -0.0506 0.0586 1.0000 14.500 1.6467 0.03948 0.03374 -0.0499 0.0561 1.0000 14.750 1.6476 0.04185 0.03614 -0.0492 0.0528 1.0000 15.000 1.6472 0.04441 0.03873 -0.0485 0.0495 1.0000 15.250 1.6480 0.04693 0.04130 -0.0480 0.0461 1.0000 15.500 1.6439 0.05003 0.04442 -0.0475 0.0424 1.0000 15.750 1.6420 0.05294 0.04738 -0.0471 0.0389 1.0000 16.000 1.6355 0.05644 0.05091 -0.0468 0.0352 1.0000 16.250 1.6286 0.06007 0.05458 -0.0467 0.0315 1.0000 16.500 1.6202 0.06394 0.05850 -0.0466 0.0280 1.0000 16.750 1.6100 0.06808 0.06268 -0.0467 0.0251 1.0000 17.000 1.6008 0.07219 0.06685 -0.0469 0.0228 1.0000 17.250 1.5915 0.07639 0.07111 -0.0473 0.0212 1.0000 17.500 1.5824 0.08062 0.07541 -0.0477 0.0197 1.0000 17.750 1.5733 0.08493 0.07979 -0.0483 0.0189 1.0000