XFOIL Version 6.96 Calculated polar for: GOE 288 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 ------ -------- --------- --------- -------- -------- -------- -15.750 -0.6403 0.09383 0.09050 -0.0639 1.0000 0.0280 -15.500 -0.6794 0.08321 0.07968 -0.0706 1.0000 0.0281 -15.250 -0.7008 0.07601 0.07234 -0.0753 1.0000 0.0282 -15.000 -0.7170 0.06993 0.06615 -0.0793 1.0000 0.0283 -14.750 -0.7309 0.06462 0.06074 -0.0827 1.0000 0.0283 -14.500 -0.7436 0.05984 0.05586 -0.0858 1.0000 0.0284 -14.250 -0.7552 0.05547 0.05141 -0.0884 1.0000 0.0285 -14.000 -0.7671 0.05146 0.04732 -0.0905 1.0000 0.0286 -13.750 -0.7716 0.04737 0.04314 -0.0940 0.9953 0.0287 -13.500 -0.7668 0.04318 0.03885 -0.0993 0.9848 0.0288 -13.250 -0.7599 0.03921 0.03476 -0.1045 0.9715 0.0289 -13.000 -0.7524 0.03535 0.03077 -0.1097 0.9552 0.0291 -12.750 -0.7389 0.03147 0.02672 -0.1163 0.9383 0.0292 -12.500 -0.7200 0.02857 0.02362 -0.1212 0.9220 0.0294 -12.250 -0.7016 0.02694 0.02183 -0.1229 0.9059 0.0297 -12.000 -0.6819 0.02565 0.02038 -0.1238 0.8902 0.0299 -11.750 -0.6612 0.02456 0.01914 -0.1243 0.8749 0.0300 -11.500 -0.6395 0.02360 0.01802 -0.1247 0.8593 0.0302 -11.250 -0.6183 0.02256 0.01686 -0.1249 0.8429 0.0304 -11.000 -0.5962 0.02163 0.01583 -0.1251 0.8257 0.0306 -10.750 -0.5729 0.02084 0.01492 -0.1253 0.8072 0.0309 -10.500 -0.5488 0.02015 0.01410 -0.1254 0.7875 0.0311 -10.250 -0.5242 0.01953 0.01334 -0.1255 0.7671 0.0314 -10.000 -0.4991 0.01897 0.01265 -0.1256 0.7471 0.0317 -9.750 -0.4734 0.01845 0.01199 -0.1257 0.7287 0.0320 -9.500 -0.4474 0.01796 0.01138 -0.1258 0.7121 0.0323 -9.250 -0.4209 0.01750 0.01080 -0.1259 0.6968 0.0326 -9.000 -0.3940 0.01706 0.01024 -0.1261 0.6834 0.0330 -8.750 -0.3668 0.01664 0.00972 -0.1263 0.6716 0.0334 -8.500 -0.3393 0.01626 0.00923 -0.1264 0.6604 0.0337 -8.250 -0.3115 0.01590 0.00877 -0.1266 0.6507 0.0341 -8.000 -0.2836 0.01558 0.00834 -0.1268 0.6409 0.0344 -7.750 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0.3272 0.01122 0.00340 -0.1321 0.5235 0.1488 -2.250 0.3864 0.01094 0.00325 -0.1328 0.5154 0.1874 -2.000 0.4157 0.01083 0.00321 -0.1331 0.5107 0.2137 -1.750 0.4447 0.01076 0.00320 -0.1333 0.5064 0.2446 -1.500 0.4741 0.01072 0.00321 -0.1335 0.5028 0.2684 -1.250 0.5036 0.01071 0.00323 -0.1337 0.4988 0.2858 -1.000 0.5330 0.01071 0.00325 -0.1339 0.4944 0.2984 -0.750 0.5620 0.01075 0.00328 -0.1340 0.4897 0.3084 -0.500 0.5910 0.01080 0.00330 -0.1341 0.4850 0.3183 -0.250 0.6203 0.01083 0.00333 -0.1343 0.4796 0.3257 0.000 0.6492 0.01088 0.00337 -0.1344 0.4736 0.3330 0.250 0.6777 0.01096 0.00340 -0.1345 0.4683 0.3393 0.500 0.7069 0.01099 0.00345 -0.1346 0.4627 0.3460 0.750 0.7355 0.01106 0.00350 -0.1347 0.4560 0.3530 1.000 0.7638 0.01115 0.00355 -0.1347 0.4495 0.3592 1.250 0.7924 0.01121 0.00363 -0.1348 0.4416 0.3683 1.500 0.8202 0.01134 0.00371 -0.1347 0.4328 0.3776 1.750 0.8482 0.01143 0.00380 -0.1347 0.4217 0.3850 2.000 0.8755 0.01157 0.00389 -0.1346 0.4095 0.3906 2.250 0.9024 0.01175 0.00399 -0.1344 0.3959 0.3951 2.500 0.9289 0.01195 0.00413 -0.1342 0.3824 0.3993 2.750 0.9552 0.01215 0.00428 -0.1340 0.3697 0.4045 3.000 0.9816 0.01236 0.00444 -0.1337 0.3592 0.4103 3.500 1.0338 0.01278 0.00480 -0.1332 0.3425 0.4211 3.750 1.0595 0.01300 0.00501 -0.1328 0.3354 0.4272 4.000 1.0855 0.01321 0.00520 -0.1325 0.3297 0.4338 4.250 1.1114 0.01339 0.00540 -0.1323 0.3242 0.4417 4.500 1.1366 0.01363 0.00563 -0.1319 0.3191 0.4504 4.750 1.1617 0.01385 0.00587 -0.1314 0.3149 0.4593 5.000 1.1876 0.01401 0.00607 -0.1312 0.3118 0.4705 5.250 1.2130 0.01419 0.00631 -0.1308 0.3085 0.4847 5.500 1.2379 0.01439 0.00656 -0.1304 0.3053 0.5039 5.750 1.2620 0.01461 0.00684 -0.1298 0.3022 0.5302 6.000 1.2855 0.01483 0.00715 -0.1292 0.2992 0.5677 6.250 1.3100 0.01494 0.00745 -0.1288 0.2970 0.6327 6.500 1.3273 0.01451 0.00769 -0.1266 0.2949 1.0000 6.750 1.3509 0.01477 0.00796 -0.1259 0.2924 1.0000 7.000 1.3736 0.01506 0.00825 -0.1252 0.2898 1.0000 7.250 1.3953 0.01538 0.00856 -0.1242 0.2874 1.0000 7.500 1.4151 0.01572 0.00890 -0.1229 0.2852 1.0000 7.750 1.4337 0.01610 0.00928 -0.1214 0.2830 1.0000 8.000 1.4523 0.01650 0.00969 -0.1200 0.2810 1.0000 8.250 1.4734 0.01682 0.01004 -0.1190 0.2797 1.0000 8.500 1.4940 0.01716 0.01042 -0.1180 0.2780 1.0000 8.750 1.5140 0.01753 0.01083 -0.1169 0.2758 1.0000 9.000 1.5332 0.01795 0.01128 -0.1158 0.2735 1.0000 9.250 1.5517 0.01842 0.01177 -0.1146 0.2713 1.0000 9.500 1.5692 0.01894 0.01231 -0.1133 0.2692 1.0000 9.750 1.5854 0.01955 0.01292 -0.1119 0.2667 1.0000 10.000 1.6012 0.02020 0.01360 -0.1105 0.2641 1.0000 10.250 1.6204 0.02068 0.01414 -0.1095 0.2623 1.0000 10.500 1.6383 0.02125 0.01476 -0.1085 0.2607 1.0000 10.750 1.6556 0.02186 0.01542 -0.1074 0.2590 1.0000 11.000 1.6722 0.02253 0.01615 -0.1063 0.2571 1.0000 11.250 1.6876 0.02329 0.01694 -0.1052 0.2547 1.0000 11.500 1.7011 0.02418 0.01785 -0.1039 0.2519 1.0000 11.750 1.7126 0.02525 0.01894 -0.1025 0.2489 1.0000 12.000 1.7283 0.02606 0.01983 -0.1016 0.2467 1.0000 12.250 1.7436 0.02692 0.02075 -0.1007 0.2440 1.0000 12.500 1.7571 0.02793 0.02182 -0.0997 0.2410 1.0000 12.750 1.7686 0.02911 0.02304 -0.0986 0.2378 1.0000 13.000 1.7773 0.03055 0.02450 -0.0974 0.2344 1.0000 13.250 1.7882 0.03185 0.02586 -0.0965 0.2312 1.0000 13.500 1.8001 0.03309 0.02718 -0.0956 0.2280 1.0000 13.750 1.8096 0.03456 0.02872 -0.0947 0.2245 1.0000 14.000 1.8150 0.03644 0.03063 -0.0937 0.2203 1.0000 14.250 1.8215 0.03828 0.03251 -0.0929 0.2162 1.0000 14.500 1.8285 0.04010 0.03440 -0.0921 0.2107 1.0000 14.750 1.8288 0.04262 0.03694 -0.0912 0.2049 1.0000 15.000 1.8322 0.04488 0.03926 -0.0905 0.1985 1.0000 15.250 1.8269 0.04812 0.04251 -0.0897 0.1901 1.0000 15.500 1.8219 0.05135 0.04576 -0.0889 0.1795 1.0000 15.750 1.8079 0.05564 0.05003 -0.0882 0.1665 1.0000 16.000 1.7873 0.06078 0.05514 -0.0875 0.1513 1.0000 16.250 1.7517 0.06776 0.06205 -0.0869 0.1296 1.0000 16.500 1.7188 0.07470 0.06896 -0.0867 0.1135 1.0000 16.750 1.6912 0.08117 0.07544 -0.0867 0.1017 1.0000 17.000 1.6695 0.08706 0.08136 -0.0869 0.0941 1.0000