XFOIL Version 6.96 Calculated polar for: GOE 798 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 = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -17.750 -0.6705 0.08750 0.08437 -0.1114 0.9345 0.0350 -17.500 -0.7448 0.07418 0.07086 -0.1194 0.9287 0.0352 -17.250 -0.9686 0.03930 0.03524 -0.1440 0.9165 0.0348 -17.000 -0.9874 0.03295 0.02867 -0.1500 0.9083 0.0350 -16.750 -0.9915 0.02978 0.02534 -0.1519 0.9003 0.0351 -16.500 -0.9893 0.02765 0.02310 -0.1526 0.8931 0.0353 -16.250 -0.9839 0.02610 0.02143 -0.1523 0.8849 0.0356 -16.000 -0.9756 0.02490 0.02013 -0.1515 0.8778 0.0358 -15.750 -0.9655 0.02389 0.01902 -0.1505 0.8698 0.0361 -15.500 -0.9541 0.02304 0.01807 -0.1493 0.8619 0.0363 -15.250 -0.9415 0.02229 0.01724 -0.1479 0.8533 0.0366 -15.000 -0.9299 0.02167 0.01651 -0.1460 0.8431 0.0368 -14.750 -0.9155 0.02112 0.01587 -0.1444 0.8313 0.0369 -14.500 -0.8997 0.02049 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0.0848 -4.750 0.1001 0.01055 0.00377 -0.1331 0.6272 0.0872 -4.500 0.1292 0.01048 0.00370 -0.1333 0.6247 0.0887 -4.250 0.1579 0.01041 0.00364 -0.1334 0.6216 0.0904 -4.000 0.1864 0.01036 0.00359 -0.1335 0.6178 0.0919 -3.750 0.2147 0.01034 0.00354 -0.1336 0.6140 0.0933 -3.500 0.2426 0.01033 0.00350 -0.1335 0.6102 0.0947 -3.250 0.2713 0.01030 0.00346 -0.1337 0.6073 0.0957 -3.000 0.3001 0.01026 0.00341 -0.1339 0.6041 0.0964 -2.750 0.3282 0.01017 0.00333 -0.1339 0.6004 0.0976 -2.500 0.3561 0.01012 0.00328 -0.1339 0.5966 0.0991 -2.250 0.3834 0.01010 0.00324 -0.1338 0.5924 0.1004 -2.000 0.4112 0.01008 0.00321 -0.1338 0.5880 0.1014 -1.750 0.4394 0.01004 0.00317 -0.1339 0.5831 0.1024 -1.500 0.4668 0.01003 0.00314 -0.1338 0.5777 0.1034 -1.250 0.4937 0.01004 0.00312 -0.1336 0.5732 0.1042 -1.000 0.5214 0.01003 0.00310 -0.1336 0.5699 0.1049 -0.750 0.5495 0.01002 0.00309 -0.1336 0.5664 0.1056 -0.500 0.5768 0.00998 0.00306 -0.1336 0.5621 0.1074 -0.250 0.6034 0.00997 0.00304 -0.1333 0.5575 0.1085 0.000 0.6294 0.00999 0.00304 -0.1330 0.5529 0.1094 0.250 0.6569 0.00998 0.00304 -0.1330 0.5489 0.1102 0.500 0.6835 0.00998 0.00305 -0.1328 0.5436 0.1111 0.750 0.7088 0.01003 0.00307 -0.1323 0.5377 0.1121 1.000 0.7343 0.01007 0.00310 -0.1319 0.5321 0.1131 1.250 0.7597 0.01011 0.00313 -0.1314 0.5248 0.1141 1.500 0.7824 0.01021 0.00319 -0.1305 0.5164 0.1150 2.000 0.8249 0.01038 0.00332 -0.1279 0.4979 0.1181 2.250 0.8448 0.01047 0.00340 -0.1264 0.4875 0.1206 2.500 0.8632 0.01063 0.00352 -0.1246 0.4765 0.1235 2.750 0.8816 0.01085 0.00369 -0.1229 0.4632 0.1270 3.000 0.9017 0.01107 0.00389 -0.1215 0.4491 0.1360 3.250 0.9211 0.01129 0.00415 -0.1201 0.4343 0.1695 3.500 0.9395 0.01155 0.00445 -0.1186 0.4192 0.2081 3.750 0.9577 0.01186 0.00477 -0.1171 0.4045 0.2381 4.000 0.9755 0.01218 0.00512 -0.1156 0.3908 0.2778 4.500 1.0132 0.01271 0.00584 -0.1130 0.3671 0.3942 4.750 1.0318 0.01284 0.00628 -0.1119 0.3569 0.5381 5.000 1.0501 0.01250 0.00677 -0.1106 0.3498 0.8369 5.250 1.0725 0.01267 0.00720 -0.1097 0.3425 1.0000 5.500 1.0893 0.01314 0.00762 -0.1081 0.3353 1.0000 5.750 1.1099 0.01348 0.00794 -0.1072 0.3310 1.0000 6.000 1.1298 0.01386 0.00830 -0.1062 0.3271 1.0000 6.250 1.1486 0.01430 0.00871 -0.1050 0.3231 1.0000 6.500 1.1670 0.01478 0.00916 -0.1038 0.3187 1.0000 6.750 1.1870 0.01519 0.00957 -0.1029 0.3158 1.0000 7.000 1.2074 0.01560 0.00998 -0.1021 0.3132 1.0000 7.250 1.2275 0.01603 0.01041 -0.1013 0.3106 1.0000 7.500 1.2469 0.01651 0.01088 -0.1004 0.3081 1.0000 7.750 1.2652 0.01704 0.01142 -0.0994 0.3057 1.0000 8.000 1.2830 0.01762 0.01198 -0.0983 0.3027 1.0000 8.250 1.2996 0.01828 0.01263 -0.0972 0.2993 1.0000 8.500 1.3194 0.01878 0.01315 -0.0965 0.2978 1.0000 8.750 1.3392 0.01929 0.01367 -0.0958 0.2959 1.0000 9.000 1.3577 0.01987 0.01427 -0.0950 0.2937 1.0000 9.250 1.3754 0.02051 0.01493 -0.0941 0.2914 1.0000 9.500 1.3930 0.02117 0.01559 -0.0932 0.2892 1.0000 9.750 1.4091 0.02195 0.01638 -0.0922 0.2870 1.0000 10.000 1.4248 0.02276 0.01720 -0.0912 0.2845 1.0000 10.250 1.4397 0.02365 0.01809 -0.0902 0.2815 1.0000 10.500 1.4578 0.02434 0.01881 -0.0895 0.2794 1.0000 10.750 1.4754 0.02508 0.01957 -0.0889 0.2768 1.0000 11.000 1.4911 0.02596 0.02047 -0.0880 0.2740 1.0000 11.250 1.5059 0.02690 0.02143 -0.0871 0.2710 1.0000 11.500 1.5190 0.02799 0.02251 -0.0861 0.2677 1.0000 11.750 1.5322 0.02909 0.02363 -0.0851 0.2646 1.0000 12.000 1.5489 0.02993 0.02450 -0.0845 0.2625 1.0000 12.250 1.5636 0.03095 0.02555 -0.0838 0.2594 1.0000 12.500 1.5768 0.03207 0.02668 -0.0829 0.2551 1.0000 12.750 1.5863 0.03349 0.02809 -0.0818 0.2504 1.0000 13.000 1.5993 0.03464 0.02927 -0.0809 0.2466 1.0000 13.250 1.6121 0.03581 0.03045 -0.0801 0.2414 1.0000 13.500 1.6187 0.03751 0.03213 -0.0789 0.2348 1.0000 13.750 1.6289 0.03890 0.03352 -0.0779 0.2276 1.0000 14.000 1.6311 0.04097 0.03556 -0.0764 0.2165 1.0000 14.250 1.6297 0.04332 0.03782 -0.0746 0.2008 1.0000 14.500 1.6254 0.04598 0.04043 -0.0728 0.1874 1.0000 14.750 1.6253 0.04832 0.04272 -0.0713 0.1780 1.0000 15.000 1.6293 0.05038 0.04479 -0.0702 0.1725 1.0000 15.250 1.6319 0.05250 0.04691 -0.0691 0.1668 1.0000 15.500 1.6351 0.05468 0.04910 -0.0680 0.1620 1.0000 15.750 1.6389 0.05679 0.05121 -0.0671 0.1574 1.0000 16.000 1.6394 0.05926 0.05369 -0.0661 0.1526 1.0000 16.250 1.6457 0.06120 0.05566 -0.0654 0.1493 1.0000 16.500 1.6521 0.06311 0.05760 -0.0648 0.1461 1.0000 16.750 1.6546 0.06546 0.05997 -0.0640 0.1434 1.0000 17.000 1.6578 0.06773 0.06227 -0.0634 0.1406 1.0000 17.250 1.6632 0.06981 0.06439 -0.0628 0.1384 1.0000 17.500 1.6687 0.07193 0.06656 -0.0624 0.1364 1.0000 17.750 1.6744 0.07399 0.06865 -0.0620 0.1342 1.0000 18.000 1.6762 0.07649 0.07120 -0.0615 0.1318 1.0000 18.250 1.6774 0.07906 0.07379 -0.0610 0.1294 1.0000 18.500 1.6796 0.08153 0.07631 -0.0606 0.1271 1.0000 18.750 1.6829 0.08394 0.07877 -0.0604 0.1252 1.0000 19.000 1.6868 0.08625 0.08113 -0.0601 0.1231 1.0000 19.250 1.6868 0.08905 0.08397 -0.0599 0.1210 1.0000