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 = 1.000 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -16.250 -0.7330 0.08507 0.08242 -0.0700 1.0000 0.0278 -16.000 -0.7622 0.07648 0.07368 -0.0758 1.0000 0.0279 -15.750 -0.7815 0.06987 0.06695 -0.0804 1.0000 0.0279 -15.500 -0.7974 0.06416 0.06114 -0.0844 1.0000 0.0280 -15.250 -0.8115 0.05907 0.05595 -0.0880 1.0000 0.0280 -15.000 -0.8232 0.05444 0.05123 -0.0912 1.0000 0.0281 -14.750 -0.8336 0.05017 0.04688 -0.0940 1.0000 0.0282 -14.500 -0.8438 0.04626 0.04289 -0.0964 1.0000 0.0282 -14.250 -0.8578 0.04278 0.03935 -0.0974 1.0000 0.0283 -14.000 -0.8673 0.03923 0.03573 -0.0994 0.9984 0.0284 -13.750 -0.8508 0.03508 0.03147 -0.1069 0.9937 0.0285 -13.500 -0.8286 0.03079 0.02705 -0.1160 0.9868 0.0287 -13.250 -0.8000 0.02785 0.02396 -0.1230 0.9812 0.0290 -13.000 -0.7783 0.02622 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0.00902 0.00279 -0.1379 0.4631 0.3748 1.500 0.8385 0.00909 0.00284 -0.1380 0.4561 0.3807 1.750 0.8673 0.00915 0.00291 -0.1381 0.4492 0.3886 2.000 0.8960 0.00926 0.00298 -0.1382 0.4400 0.3956 2.250 0.9243 0.00934 0.00305 -0.1383 0.4300 0.4027 2.500 0.9521 0.00948 0.00314 -0.1383 0.4169 0.4083 2.750 0.9794 0.00966 0.00324 -0.1382 0.4015 0.4131 3.000 1.0064 0.00986 0.00337 -0.1381 0.3852 0.4181 3.250 1.0330 0.01008 0.00353 -0.1379 0.3697 0.4245 3.500 1.0598 0.01029 0.00369 -0.1377 0.3572 0.4311 3.750 1.0863 0.01051 0.00386 -0.1375 0.3471 0.4377 4.000 1.1129 0.01070 0.00404 -0.1373 0.3388 0.4457 4.250 1.1395 0.01090 0.00422 -0.1372 0.3319 0.4536 4.500 1.1665 0.01104 0.00439 -0.1370 0.3265 0.4648 4.750 1.1926 0.01125 0.00459 -0.1368 0.3209 0.4784 5.000 1.2189 0.01142 0.00480 -0.1366 0.3161 0.4972 5.250 1.2459 0.01151 0.00497 -0.1365 0.3131 0.5257 5.500 1.2724 0.01161 0.00518 -0.1364 0.3097 0.5734 5.750 1.2983 0.01161 0.00545 -0.1363 0.3063 0.6883 6.000 1.3170 0.01133 0.00571 -0.1343 0.3027 1.0000 6.250 1.3423 0.01157 0.00593 -0.1340 0.2997 1.0000 6.500 1.3688 0.01173 0.00611 -0.1338 0.2980 1.0000 6.750 1.3947 0.01191 0.00630 -0.1335 0.2959 1.0000 7.000 1.4199 0.01213 0.00651 -0.1331 0.2935 1.0000 7.250 1.4443 0.01238 0.00676 -0.1326 0.2910 1.0000 7.500 1.4676 0.01267 0.00703 -0.1319 0.2881 1.0000 7.750 1.4888 0.01305 0.00738 -0.1309 0.2843 1.0000 8.000 1.5133 0.01324 0.00760 -0.1304 0.2825 1.0000 8.250 1.5375 0.01342 0.00781 -0.1299 0.2807 1.0000 8.500 1.5606 0.01365 0.00806 -0.1292 0.2789 1.0000 8.750 1.5819 0.01390 0.00833 -0.1281 0.2770 1.0000 9.000 1.6016 0.01420 0.00864 -0.1268 0.2750 1.0000 9.250 1.6203 0.01455 0.00900 -0.1253 0.2727 1.0000 9.500 1.6376 0.01499 0.00943 -0.1237 0.2701 1.0000 9.750 1.6539 0.01549 0.00994 -0.1220 0.2674 1.0000 10.000 1.6761 0.01573 0.01023 -0.1213 0.2661 1.0000 10.250 1.6978 0.01600 0.01054 -0.1205 0.2639 1.0000 10.500 1.7181 0.01634 0.01091 -0.1195 0.2615 1.0000 10.750 1.7368 0.01677 0.01136 -0.1184 0.2590 1.0000 11.000 1.7534 0.01731 0.01190 -0.1170 0.2560 1.0000 11.250 1.7671 0.01803 0.01261 -0.1152 0.2525 1.0000 11.500 1.7859 0.01849 0.01313 -0.1142 0.2509 1.0000 11.750 1.8054 0.01893 0.01362 -0.1134 0.2493 1.0000 12.000 1.8242 0.01941 0.01415 -0.1125 0.2469 1.0000 12.250 1.8410 0.02003 0.01479 -0.1114 0.2438 1.0000 12.500 1.8553 0.02082 0.01559 -0.1101 0.2405 1.0000 12.750 1.8658 0.02186 0.01664 -0.1084 0.2368 1.0000 13.000 1.8844 0.02242 0.01727 -0.1077 0.2345 1.0000 13.250 1.9007 0.02315 0.01804 -0.1068 0.2312 1.0000 13.500 1.9133 0.02415 0.01906 -0.1056 0.2268 1.0000 13.750 1.9210 0.02554 0.02045 -0.1040 0.2218 1.0000 14.000 1.9363 0.02640 0.02137 -0.1032 0.2181 1.0000 14.250 1.9460 0.02771 0.02270 -0.1020 0.2127 1.0000 14.500 1.9511 0.02944 0.02444 -0.1006 0.2073 1.0000 14.750 1.9606 0.03085 0.02589 -0.0996 0.2015 1.0000 15.000 1.9603 0.03314 0.02816 -0.0980 0.1937 1.0000 15.250 1.9604 0.03547 0.03050 -0.0967 0.1836 1.0000 15.500 1.9522 0.03867 0.03367 -0.0952 0.1709 1.0000 15.750 1.9346 0.04289 0.03785 -0.0935 0.1557 1.0000 16.000 1.9108 0.04792 0.04282 -0.0919 0.1387 1.0000 16.500 1.8479 0.06012 0.05494 -0.0893 0.1062 1.0000 16.750 1.8237 0.06569 0.06052 -0.0886 0.0961 1.0000 17.000 1.8038 0.07093 0.06578 -0.0882 0.0892 1.0000 17.250 1.7894 0.07562 0.07053 -0.0880 0.0844 1.0000 17.500 1.7734 0.08060 0.07556 -0.0879 0.0804 1.0000 17.750 1.7609 0.08521 0.08023 -0.0880 0.0772 1.0000