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 = 0.500 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -15.500 -0.4899 0.07423 0.07026 -0.1109 0.8728 0.0313 -15.250 -0.5262 0.06605 0.06186 -0.1161 0.8577 0.0314 -15.000 -0.5590 0.05828 0.05388 -0.1215 0.8444 0.0314 -14.750 -0.5888 0.05073 0.04612 -0.1271 0.8334 0.0315 -14.500 -0.6120 0.04355 0.03872 -0.1332 0.8229 0.0315 -14.250 -0.6246 0.03729 0.03224 -0.1397 0.8143 0.0316 -14.000 -0.6282 0.03243 0.02718 -0.1457 0.8056 0.0317 -13.500 -0.6204 0.02758 0.02202 -0.1496 0.7910 0.0319 -13.250 -0.6136 0.02634 0.02067 -0.1489 0.7838 0.0321 -13.000 -0.6014 0.02532 0.01953 -0.1482 0.7770 0.0323 -12.750 -0.5858 0.02438 0.01850 -0.1477 0.7710 0.0325 -12.500 -0.5685 0.02353 0.01756 -0.1472 0.7644 0.0327 -12.250 -0.5501 0.02277 0.01670 -0.1466 0.7582 0.0329 -12.000 -0.5304 0.02207 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0.01230 0.00437 -0.1337 0.5477 0.0816 -2.250 0.4725 0.01220 0.00429 -0.1335 0.5417 0.0847 -2.000 0.4985 0.01217 0.00422 -0.1330 0.5347 0.0881 -1.750 0.5241 0.01211 0.00417 -0.1326 0.5281 0.0924 -1.500 0.5503 0.01206 0.00413 -0.1322 0.5206 0.0972 -1.250 0.5751 0.01205 0.00413 -0.1317 0.5131 0.1064 -1.000 0.6010 0.01203 0.00418 -0.1313 0.5060 0.1262 -0.750 0.6260 0.01208 0.00421 -0.1307 0.4977 0.1381 -0.500 0.6505 0.01216 0.00425 -0.1301 0.4898 0.1456 -0.250 0.6750 0.01222 0.00430 -0.1294 0.4808 0.1527 0.000 0.6983 0.01234 0.00436 -0.1285 0.4727 0.1579 0.250 0.7227 0.01240 0.00441 -0.1279 0.4653 0.1638 0.500 0.7456 0.01252 0.00450 -0.1270 0.4583 0.1695 0.750 0.7688 0.01262 0.00458 -0.1262 0.4522 0.1740 1.000 0.7910 0.01271 0.00466 -0.1251 0.4458 0.1794 1.250 0.8114 0.01286 0.00477 -0.1238 0.4395 0.1853 1.500 0.8335 0.01297 0.00489 -0.1228 0.4346 0.1940 1.750 0.8568 0.01306 0.00502 -0.1220 0.4300 0.2075 2.000 0.8794 0.01318 0.00520 -0.1212 0.4250 0.2318 2.250 0.9015 0.01334 0.00541 -0.1204 0.4201 0.2638 2.500 0.9251 0.01346 0.00561 -0.1198 0.4161 0.2997 2.750 0.9494 0.01354 0.00581 -0.1194 0.4123 0.3435 3.000 0.9729 0.01360 0.00606 -0.1190 0.4082 0.4156 3.250 0.9953 0.01368 0.00636 -0.1183 0.4040 0.5076 3.500 1.0164 0.01386 0.00667 -0.1174 0.3999 0.5732 3.750 1.0399 0.01392 0.00693 -0.1169 0.3965 0.6407 4.000 1.0611 0.01347 0.00727 -0.1155 0.3929 1.0000 4.250 1.0827 0.01377 0.00753 -0.1147 0.3890 1.0000 4.500 1.1032 0.01411 0.00783 -0.1137 0.3851 1.0000 4.750 1.1231 0.01449 0.00815 -0.1127 0.3816 1.0000 5.000 1.1450 0.01481 0.00845 -0.1120 0.3788 1.0000 5.250 1.1673 0.01511 0.00875 -0.1114 0.3758 1.0000 5.500 1.1888 0.01545 0.00908 -0.1106 0.3724 1.0000 5.750 1.2093 0.01584 0.00944 -0.1098 0.3690 1.0000 6.000 1.2286 0.01629 0.00986 -0.1089 0.3657 1.0000 6.250 1.2471 0.01679 0.01033 -0.1078 0.3624 1.0000 6.500 1.2684 0.01718 0.01072 -0.1072 0.3597 1.0000 6.750 1.2891 0.01759 0.01115 -0.1066 0.3565 1.0000 7.000 1.3089 0.01806 0.01161 -0.1058 0.3531 1.0000 7.250 1.3274 0.01861 0.01215 -0.1050 0.3498 1.0000 7.500 1.3445 0.01924 0.01276 -0.1040 0.3463 1.0000 7.750 1.3622 0.01985 0.01336 -0.1031 0.3431 1.0000 8.000 1.3818 0.02038 0.01391 -0.1025 0.3399 1.0000 8.250 1.4003 0.02097 0.01452 -0.1017 0.3363 1.0000 8.500 1.4170 0.02168 0.01522 -0.1008 0.3328 1.0000 8.750 1.4322 0.02249 0.01601 -0.0998 0.3292 1.0000 9.000 1.4477 0.02329 0.01682 -0.0989 0.3258 1.0000 9.250 1.4653 0.02398 0.01753 -0.0982 0.3221 1.0000 9.500 1.4812 0.02478 0.01835 -0.0974 0.3180 1.0000 9.750 1.4945 0.02577 0.01934 -0.0964 0.3139 1.0000 10.000 1.5065 0.02686 0.02041 -0.0953 0.3101 1.0000 10.250 1.5230 0.02767 0.02126 -0.0946 0.3068 1.0000 10.500 1.5372 0.02864 0.02226 -0.0938 0.3027 1.0000 10.750 1.5492 0.02979 0.02340 -0.0928 0.2983 1.0000 11.000 1.5576 0.03123 0.02483 -0.0916 0.2938 1.0000 11.250 1.5721 0.03223 0.02587 -0.0910 0.2898 1.0000 11.500 1.5831 0.03353 0.02719 -0.0901 0.2851 1.0000 11.750 1.5916 0.03502 0.02868 -0.0890 0.2807 1.0000 12.000 1.6001 0.03655 0.03022 -0.0881 0.2768 1.0000 12.250 1.6116 0.03784 0.03155 -0.0873 0.2729 1.0000 12.500 1.6205 0.03940 0.03313 -0.0865 0.2685 1.0000 12.750 1.6258 0.04127 0.03501 -0.0855 0.2642 1.0000 13.000 1.6336 0.04294 0.03670 -0.0847 0.2604 1.0000 13.250 1.6421 0.04458 0.03838 -0.0839 0.2563 1.0000 13.500 1.6476 0.04650 0.04032 -0.0831 0.2518 1.0000 13.750 1.6494 0.04880 0.04262 -0.0821 0.2477 1.0000 14.000 1.6580 0.05047 0.04434 -0.0815 0.2444 1.0000 14.250 1.6641 0.05241 0.04632 -0.0809 0.2409 1.0000 14.500 1.6689 0.05447 0.04840 -0.0802 0.2373 1.0000 14.750 1.6695 0.05695 0.05091 -0.0794 0.2338 1.0000 15.000 1.6743 0.05905 0.05304 -0.0788 0.2308 1.0000 15.250 1.6806 0.06102 0.05507 -0.0783 0.2279 1.0000 15.500 1.6841 0.06330 0.05740 -0.0778 0.2247 1.0000 15.750 1.6857 0.06575 0.05987 -0.0772 0.2214 1.0000 16.000 1.6834 0.06865 0.06279 -0.0766 0.2181 1.0000 16.250 1.6887 0.07077 0.06496 -0.0763 0.2157 1.0000 16.500 1.6923 0.07309 0.06735 -0.0759 0.2131 1.0000 16.750 1.6944 0.07559 0.06990 -0.0756 0.2102 1.0000 17.000 1.6944 0.07832 0.07267 -0.0753 0.2073 1.0000 17.250 1.6912 0.08141 0.07578 -0.0749 0.2043 1.0000 17.500 1.6937 0.08389 0.07831 -0.0747 0.2018 1.0000 17.750 1.6948 0.08659 0.08108 -0.0746 0.1990 1.0000 18.000 1.6948 0.08941 0.08395 -0.0746 0.1958 1.0000 18.250 1.6907 0.09272 0.08729 -0.0745 0.1926 1.0000