XFOIL Version 6.96 Calculated polar for: GOE 390 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 ------ -------- --------- --------- -------- -------- -------- -16.750 -0.5678 0.07685 0.07401 -0.1128 0.9760 0.0311 -16.500 -0.6083 0.06781 0.06480 -0.1189 0.9659 0.0311 -16.250 -0.6420 0.06042 0.05724 -0.1235 0.9539 0.0312 -16.000 -0.6705 0.05377 0.05044 -0.1276 0.9409 0.0312 -15.750 -0.6952 0.04741 0.04390 -0.1320 0.9256 0.0312 -15.500 -0.7140 0.04145 0.03775 -0.1365 0.9067 0.0313 -15.250 -0.7264 0.03609 0.03217 -0.1413 0.8845 0.0314 -15.000 -0.7315 0.03156 0.02741 -0.1461 0.8643 0.0315 -14.750 -0.7314 0.02823 0.02389 -0.1497 0.8484 0.0316 -14.500 -0.7275 0.02612 0.02161 -0.1510 0.8358 0.0318 -14.250 -0.7197 0.02468 0.02006 -0.1509 0.8260 0.0320 -14.000 -0.7111 0.02367 0.01894 -0.1498 0.8173 0.0321 -13.750 -0.6964 0.02277 0.01798 -0.1491 0.8107 0.0323 -13.500 -0.6794 0.02198 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-4.000 0.2957 0.01041 0.00384 -0.1375 0.5912 0.0720 -3.750 0.3241 0.01030 0.00375 -0.1375 0.5871 0.0742 -3.500 0.3521 0.01026 0.00368 -0.1374 0.5825 0.0762 -3.250 0.3794 0.01020 0.00358 -0.1372 0.5777 0.0780 -3.000 0.4066 0.01010 0.00348 -0.1370 0.5731 0.0803 -2.750 0.4351 0.01001 0.00339 -0.1371 0.5691 0.0823 -2.500 0.4631 0.00996 0.00332 -0.1370 0.5640 0.0841 -2.250 0.4898 0.00989 0.00323 -0.1367 0.5582 0.0870 -2.000 0.5170 0.00983 0.00317 -0.1365 0.5527 0.0900 -1.750 0.5450 0.00976 0.00311 -0.1364 0.5470 0.0937 -1.500 0.5717 0.00970 0.00306 -0.1362 0.5405 0.1011 -1.250 0.5980 0.00965 0.00308 -0.1359 0.5340 0.1227 -1.000 0.6257 0.00962 0.00311 -0.1358 0.5271 0.1412 -0.750 0.6515 0.00967 0.00314 -0.1353 0.5186 0.1509 -0.500 0.6785 0.00972 0.00316 -0.1351 0.5104 0.1570 -0.250 0.7039 0.00977 0.00319 -0.1346 0.5008 0.1643 0.000 0.7300 0.00983 0.00323 -0.1343 0.4922 0.1695 0.250 0.7547 0.00993 0.00328 -0.1337 0.4822 0.1748 0.500 0.7800 0.01000 0.00334 -0.1332 0.4736 0.1807 0.750 0.8042 0.01012 0.00341 -0.1325 0.4644 0.1859 1.000 0.8289 0.01020 0.00350 -0.1320 0.4570 0.1950 1.250 0.8536 0.01029 0.00358 -0.1314 0.4499 0.2065 1.500 0.8756 0.01040 0.00372 -0.1304 0.4424 0.2310 1.750 0.9000 0.01037 0.00381 -0.1298 0.4376 0.2764 2.000 0.9227 0.01039 0.00393 -0.1290 0.4323 0.3237 2.250 0.9438 0.01043 0.00410 -0.1279 0.4264 0.3857 2.500 0.9676 0.01037 0.00430 -0.1273 0.4219 0.4911 2.750 0.9927 0.01036 0.00448 -0.1270 0.4177 0.5699 3.000 1.0165 0.01041 0.00467 -0.1264 0.4131 0.6337 3.250 1.0374 0.01030 0.00498 -0.1253 0.4084 0.7961 3.500 1.0652 0.01021 0.00524 -0.1252 0.4044 1.0000 3.750 1.0897 0.01036 0.00538 -0.1247 0.4015 1.0000 4.000 1.1130 0.01055 0.00554 -0.1240 0.3982 1.0000 4.250 1.1354 0.01078 0.00574 -0.1232 0.3947 1.0000 4.500 1.1564 0.01108 0.00598 -0.1222 0.3907 1.0000 4.750 1.1773 0.01138 0.00625 -0.1212 0.3868 1.0000 5.000 1.2021 0.01155 0.00642 -0.1209 0.3847 1.0000 5.250 1.2261 0.01176 0.00663 -0.1205 0.3820 1.0000 5.500 1.2486 0.01202 0.00687 -0.1198 0.3788 1.0000 5.750 1.2697 0.01234 0.00716 -0.1189 0.3754 1.0000 6.000 1.2895 0.01272 0.00751 -0.1179 0.3715 1.0000 6.250 1.3108 0.01306 0.00783 -0.1172 0.3685 1.0000 6.500 1.3345 0.01329 0.00808 -0.1168 0.3663 1.0000 6.750 1.3571 0.01358 0.00837 -0.1163 0.3634 1.0000 7.000 1.3785 0.01392 0.00870 -0.1156 0.3601 1.0000 7.250 1.3979 0.01436 0.00912 -0.1147 0.3567 1.0000 7.500 1.4155 0.01490 0.00963 -0.1135 0.3529 1.0000 7.750 1.4371 0.01526 0.01000 -0.1130 0.3504 1.0000 8.000 1.4591 0.01560 0.01036 -0.1125 0.3477 1.0000 8.250 1.4795 0.01603 0.01080 -0.1119 0.3444 1.0000 8.500 1.4983 0.01655 0.01130 -0.1111 0.3407 1.0000 8.750 1.5142 0.01723 0.01197 -0.1099 0.3368 1.0000 9.000 1.5325 0.01780 0.01254 -0.1091 0.3336 1.0000 9.250 1.5532 0.01825 0.01302 -0.1086 0.3309 1.0000 9.500 1.5720 0.01882 0.01360 -0.1079 0.3274 1.0000 9.750 1.5885 0.01952 0.01429 -0.1070 0.3235 1.0000 10.000 1.6013 0.02046 0.01521 -0.1058 0.3189 1.0000 10.250 1.6197 0.02107 0.01585 -0.1052 0.3157 1.0000 10.500 1.6371 0.02177 0.01656 -0.1045 0.3120 1.0000 10.750 1.6521 0.02261 0.01740 -0.1036 0.3078 1.0000 11.000 1.6630 0.02374 0.01852 -0.1023 0.3031 1.0000 11.250 1.6783 0.02460 0.01940 -0.1015 0.2995 1.0000 11.500 1.6941 0.02543 0.02026 -0.1008 0.2956 1.0000 11.750 1.7057 0.02658 0.02141 -0.0997 0.2910 1.0000 12.000 1.7134 0.02801 0.02282 -0.0984 0.2857 1.0000 12.250 1.7277 0.02899 0.02383 -0.0976 0.2821 1.0000 12.500 1.7396 0.03015 0.02500 -0.0967 0.2774 1.0000 12.750 1.7454 0.03181 0.02665 -0.0954 0.2723 1.0000 13.000 1.7553 0.03316 0.02802 -0.0944 0.2681 1.0000 13.250 1.7660 0.03448 0.02937 -0.0936 0.2641 1.0000 13.500 1.7729 0.03610 0.03100 -0.0925 0.2596 1.0000 13.750 1.7740 0.03825 0.03314 -0.0911 0.2545 1.0000 14.000 1.7863 0.03949 0.03442 -0.0905 0.2515 1.0000 14.250 1.7938 0.04115 0.03611 -0.0896 0.2477 1.0000 14.500 1.7968 0.04320 0.03817 -0.0885 0.2434 1.0000 14.750 1.7973 0.04551 0.04049 -0.0874 0.2391 1.0000 15.000 1.8073 0.04700 0.04203 -0.0868 0.2361 1.0000 15.250 1.8119 0.04899 0.04404 -0.0860 0.2324 1.0000 15.500 1.8119 0.05143 0.04650 -0.0850 0.2284 1.0000 15.750 1.8108 0.05400 0.04908 -0.0840 0.2244 1.0000 16.000 1.8188 0.05571 0.05084 -0.0835 0.2215 1.0000 16.250 1.8219 0.05789 0.05306 -0.0828 0.2180 1.0000 16.500 1.8186 0.06076 0.05594 -0.0819 0.2142 1.0000 16.750 1.8153 0.06364 0.05884 -0.0811 0.2105 1.0000 17.000 1.8217 0.06557 0.06083 -0.0807 0.2081 1.0000 17.250 1.8254 0.06775 0.06305 -0.0803 0.2050 1.0000 17.500 1.8216 0.07078 0.06611 -0.0796 0.2019 1.0000 17.750 1.8162 0.07395 0.06929 -0.0790 0.1984 1.0000 18.000 1.8164 0.07661 0.07201 -0.0787 0.1960 1.0000 18.250 1.8213 0.07874 0.07420 -0.0784 0.1937 1.0000 18.500 1.8214 0.08140 0.07690 -0.0782 0.1912 1.0000 18.750 1.8177 0.08449 0.08003 -0.0779 0.1886 1.0000 19.000 1.8103 0.08805 0.08362 -0.0776 0.1857 1.0000