XFOIL Version 6.96 Calculated polar for: GOE 682 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -12.500 -0.3838 0.12228 0.11975 -0.0342 1.0000 0.0146 -12.250 -0.3783 0.11966 0.11715 -0.0349 1.0000 0.0150 -11.250 -0.7205 0.03092 0.02768 -0.0958 0.9850 0.0215 -11.000 -0.7031 0.02787 0.02430 -0.0979 0.9790 0.0220 -10.750 -0.6741 0.02703 0.02342 -0.0994 0.9762 0.0225 -10.500 -0.6442 0.02666 0.02302 -0.1005 0.9733 0.0229 -10.250 -0.6166 0.02604 0.02234 -0.1013 0.9688 0.0234 -10.000 -0.5871 0.02502 0.02119 -0.1029 0.9657 0.0240 -9.750 -0.5607 0.02382 0.01981 -0.1039 0.9611 0.0247 -9.500 -0.5343 0.02251 0.01827 -0.1049 0.9558 0.0255 -9.250 -0.5063 0.02120 0.01670 -0.1060 0.9512 0.0261 -9.000 -0.4799 0.02027 0.01556 -0.1064 0.9445 0.0266 -8.750 -0.4529 0.01891 0.01400 -0.1072 0.9391 0.0272 -8.500 -0.4273 0.01808 0.01307 -0.1072 0.9316 0.0278 -8.250 -0.3988 0.01748 0.01237 -0.1077 0.9251 0.0282 -8.000 -0.3722 0.01697 0.01177 -0.1077 0.9166 0.0288 -7.750 -0.3451 0.01645 0.01114 -0.1077 0.9087 0.0294 -7.500 -0.3189 0.01583 0.01039 -0.1076 0.9000 0.0299 -7.250 -0.2931 0.01522 0.00964 -0.1073 0.8914 0.0304 -7.000 -0.2670 0.01464 0.00891 -0.1070 0.8822 0.0309 -6.750 -0.2415 0.01412 0.00826 -0.1066 0.8724 0.0315 -6.500 -0.2151 0.01371 0.00771 -0.1063 0.8632 0.0320 -6.250 -0.1891 0.01332 0.00722 -0.1059 0.8534 0.0325 -6.000 -0.1631 0.01293 0.00670 -0.1055 0.8439 0.0328 -5.750 -0.1382 0.01231 0.00597 -0.1049 0.8331 0.0335 -5.500 -0.1128 0.01191 0.00549 -0.1044 0.8208 0.0341 -5.250 -0.0871 0.01161 0.00512 -0.1038 0.8076 0.0347 -5.000 -0.0614 0.01136 0.00477 -0.1033 0.7934 0.0354 -4.750 -0.0355 0.01113 0.00446 -0.1028 0.7804 0.0361 -4.500 -0.0095 0.01092 0.00415 -0.1023 0.7689 0.0369 -4.250 0.0168 0.01071 0.00387 -0.1019 0.7584 0.0378 -4.000 0.0433 0.01054 0.00363 -0.1014 0.7484 0.0388 -3.500 0.0960 0.01016 0.00311 -0.1006 0.7288 0.0409 -3.250 0.1222 0.00997 0.00288 -0.1002 0.7195 0.0425 -3.000 0.1488 0.00984 0.00271 -0.0998 0.7096 0.0442 -2.750 0.1755 0.00973 0.00255 -0.0994 0.7004 0.0463 -2.500 0.2021 0.00964 0.00241 -0.0990 0.6918 0.0483 -2.250 0.2289 0.00951 0.00226 -0.0987 0.6835 0.0516 -1.750 0.2824 0.00937 0.00206 -0.0980 0.6662 0.0600 -1.500 0.3089 0.00928 0.00196 -0.0976 0.6583 0.0674 -1.250 0.3357 0.00922 0.00188 -0.0973 0.6489 0.0747 -1.000 0.3620 0.00916 0.00181 -0.0969 0.6386 0.0862 -0.750 0.3878 0.00903 0.00177 -0.0964 0.6279 0.1192 -0.500 0.4140 0.00893 0.00176 -0.0960 0.6177 0.1619 -0.250 0.4401 0.00890 0.00177 -0.0956 0.6068 0.1904 0.000 0.4663 0.00887 0.00177 -0.0952 0.5960 0.2141 0.250 0.4927 0.00885 0.00178 -0.0948 0.5852 0.2363 0.500 0.5187 0.00882 0.00180 -0.0944 0.5730 0.2645 0.750 0.5442 0.00879 0.00182 -0.0939 0.5590 0.3012 1.000 0.5691 0.00872 0.00185 -0.0933 0.5427 0.3614 1.250 0.5911 0.00830 0.00194 -0.0923 0.5286 0.5608 1.500 0.6057 0.00756 0.00208 -0.0892 0.5163 0.8632 2.000 0.6987 0.00779 0.00223 -0.0973 0.4816 1.0000 2.250 0.7224 0.00797 0.00231 -0.0964 0.4658 1.0000 2.500 0.7462 0.00815 0.00240 -0.0955 0.4519 1.0000 2.750 0.7704 0.00832 0.00250 -0.0947 0.4397 1.0000 3.000 0.7948 0.00849 0.00260 -0.0940 0.4286 1.0000 3.250 0.8191 0.00867 0.00273 -0.0932 0.4181 1.0000 3.500 0.8433 0.00885 0.00285 -0.0924 0.4071 1.0000 3.750 0.8678 0.00903 0.00298 -0.0917 0.3957 1.0000 4.000 0.8920 0.00923 0.00313 -0.0910 0.3836 1.0000 4.250 0.9159 0.00944 0.00329 -0.0902 0.3703 1.0000 4.500 0.9397 0.00966 0.00345 -0.0894 0.3571 1.0000 4.750 0.9633 0.00989 0.00363 -0.0886 0.3422 1.0000 5.000 0.9866 0.01014 0.00382 -0.0877 0.3257 1.0000 5.250 1.0094 0.01042 0.00403 -0.0868 0.3073 1.0000 5.500 1.0311 0.01077 0.00427 -0.0857 0.2864 1.0000 6.000 1.0743 0.01148 0.00482 -0.0835 0.2541 1.0000 6.250 1.0966 0.01178 0.00509 -0.0826 0.2441 1.0000 6.500 1.1184 0.01210 0.00539 -0.0815 0.2357 1.0000 6.750 1.1406 0.01239 0.00567 -0.0805 0.2272 1.0000 7.000 1.1617 0.01274 0.00598 -0.0794 0.2187 1.0000 7.250 1.1832 0.01305 0.00628 -0.0783 0.2100 1.0000 7.500 1.2039 0.01339 0.00661 -0.0771 0.2029 1.0000 7.750 1.2254 0.01367 0.00691 -0.0761 0.1961 1.0000 8.000 1.2451 0.01405 0.00726 -0.0747 0.1883 1.0000 8.250 1.2656 0.01436 0.00758 -0.0735 0.1795 1.0000 8.500 1.2840 0.01473 0.00794 -0.0720 0.1701 1.0000 8.750 1.3007 0.01513 0.00832 -0.0701 0.1593 1.0000 9.000 1.3160 0.01561 0.00873 -0.0681 0.1434 1.0000 9.250 1.3257 0.01637 0.00932 -0.0652 0.1145 1.0000 9.500 1.3315 0.01738 0.01014 -0.0619 0.0868 1.0000 9.750 1.3408 0.01823 0.01092 -0.0593 0.0724 1.0000 10.000 1.3504 0.01908 0.01173 -0.0567 0.0584 1.0000 10.250 1.3549 0.02026 0.01278 -0.0537 0.0384 1.0000 10.500 1.3595 0.02147 0.01392 -0.0508 0.0248 1.0000 10.750 1.3678 0.02250 0.01495 -0.0485 0.0198 1.0000 11.000 1.3768 0.02352 0.01600 -0.0465 0.0172 1.0000 11.250 1.3874 0.02447 0.01702 -0.0447 0.0160 1.0000 11.500 1.3968 0.02554 0.01815 -0.0429 0.0150 1.0000 11.750 1.4045 0.02677 0.01944 -0.0411 0.0140 1.0000 12.000 1.4122 0.02805 0.02079 -0.0394 0.0133 1.0000 12.250 1.4207 0.02931 0.02214 -0.0379 0.0128 1.0000 12.500 1.4283 0.03070 0.02360 -0.0365 0.0122 1.0000 12.750 1.4344 0.03226 0.02525 -0.0352 0.0117 1.0000 13.000 1.4391 0.03400 0.02707 -0.0339 0.0112 1.0000 13.250 1.4416 0.03601 0.02916 -0.0328 0.0107 1.0000 13.500 1.4424 0.03828 0.03152 -0.0317 0.0104 1.0000 13.750 1.4446 0.04049 0.03382 -0.0309 0.0102 1.0000 14.000 1.4463 0.04283 0.03628 -0.0302 0.0100 1.0000 14.250 1.4477 0.04530 0.03884 -0.0297 0.0097 1.0000 14.500 1.4479 0.04799 0.04164 -0.0294 0.0095 1.0000 14.750 1.4469 0.05091 0.04466 -0.0292 0.0092 1.0000 15.000 1.4445 0.05410 0.04796 -0.0293 0.0091 1.0000 15.250 1.4423 0.05738 0.05134 -0.0295 0.0088 1.0000 15.500 1.4376 0.06111 0.05519 -0.0300 0.0087 1.0000 15.750 1.4327 0.06499 0.05918 -0.0306 0.0085 1.0000 16.000 1.4273 0.06906 0.06336 -0.0315 0.0084 1.0000 16.250 1.4202 0.07352 0.06793 -0.0326 0.0083 1.0000 16.500 1.4122 0.07822 0.07274 -0.0340 0.0081 1.0000 16.750 1.4027 0.08331 0.07793 -0.0356 0.0080 1.0000 17.000 1.3901 0.08904 0.08379 -0.0376 0.0079 1.0000