XFOIL Version 6.96 Calculated polar for: GOE 535 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -11.000 -0.2470 0.09931 0.09528 -0.0556 0.9907 0.0434 -10.500 -0.4916 0.03610 0.03089 -0.1191 0.9509 0.0468 -10.250 -0.4792 0.03103 0.02522 -0.1264 0.9381 0.0480 -10.000 -0.4417 0.02997 0.02415 -0.1297 0.9338 0.0487 -9.750 -0.4171 0.02894 0.02306 -0.1305 0.9216 0.0493 -9.500 -0.3847 0.02767 0.02166 -0.1330 0.9127 0.0502 -9.250 -0.3565 0.02622 0.02002 -0.1346 0.9013 0.0513 -9.000 -0.3293 0.02460 0.01810 -0.1361 0.8902 0.0526 -8.750 -0.2974 0.02356 0.01693 -0.1376 0.8800 0.0537 -8.500 -0.2682 0.02295 0.01627 -0.1382 0.8673 0.0546 -8.250 -0.2362 0.02224 0.01545 -0.1394 0.8553 0.0558 -8.000 -0.2070 0.02140 0.01440 -0.1401 0.8410 0.0577 -7.750 -0.1786 0.02070 0.01354 -0.1404 0.8258 0.0592 -7.500 -0.1494 0.02028 0.01306 -0.1407 0.8109 0.0605 -7.250 -0.1208 0.01979 0.01242 -0.1408 0.7961 0.0621 -7.000 -0.0942 0.01920 0.01161 -0.1406 0.7802 0.0641 -6.750 -0.0676 0.01878 0.01109 -0.1403 0.7649 0.0656 -6.500 -0.0408 0.01848 0.01071 -0.1400 0.7505 0.0672 -6.250 -0.0144 0.01814 0.01022 -0.1396 0.7366 0.0694 -6.000 0.0117 0.01777 0.00968 -0.1392 0.7236 0.0716 -5.750 0.0377 0.01748 0.00933 -0.1387 0.7108 0.0732 -5.500 0.0635 0.01721 0.00899 -0.1381 0.6976 0.0754 -5.250 0.0897 0.01696 0.00859 -0.1376 0.6855 0.0778 -5.000 0.1154 0.01666 0.00822 -0.1370 0.6735 0.0799 -4.750 0.1413 0.01642 0.00795 -0.1365 0.6625 0.0821 -4.500 0.1673 0.01621 0.00765 -0.1359 0.6510 0.0847 -4.250 0.1934 0.01602 0.00734 -0.1353 0.6396 0.0871 -4.000 0.2188 0.01576 0.00706 -0.1347 0.6281 0.0894 -3.750 0.2447 0.01556 0.00683 -0.1341 0.6170 0.0919 -3.500 0.2707 0.01541 0.00658 -0.1335 0.6066 0.0946 -3.250 0.2966 0.01521 0.00635 -0.1329 0.5960 0.0970 -3.000 0.3221 0.01505 0.00614 -0.1323 0.5853 0.0997 -2.750 0.3482 0.01491 0.00597 -0.1317 0.5744 0.1028 -2.500 0.3740 0.01484 0.00579 -0.1310 0.5641 0.1059 -2.250 0.4001 0.01468 0.00563 -0.1305 0.5542 0.1094 -2.000 0.4259 0.01461 0.00550 -0.1299 0.5445 0.1136 -1.750 0.4521 0.01453 0.00538 -0.1293 0.5349 0.1187 -1.500 0.4779 0.01445 0.00528 -0.1287 0.5253 0.1259 -1.250 0.5040 0.01437 0.00519 -0.1282 0.5168 0.1369 -1.000 0.5299 0.01425 0.00513 -0.1276 0.5084 0.1621 -0.750 0.5552 0.01406 0.00506 -0.1271 0.5008 0.2181 -0.500 0.5806 0.01387 0.00519 -0.1266 0.4929 0.3096 -0.250 0.6063 0.01397 0.00532 -0.1259 0.4853 0.3567 0.000 0.6325 0.01411 0.00542 -0.1253 0.4789 0.3813 0.250 0.6588 0.01424 0.00554 -0.1247 0.4721 0.3984 0.500 0.6847 0.01439 0.00564 -0.1240 0.4656 0.4129 0.750 0.7106 0.01458 0.00577 -0.1233 0.4599 0.4280 1.000 0.7366 0.01472 0.00594 -0.1227 0.4539 0.4404 1.250 0.7626 0.01490 0.00606 -0.1221 0.4482 0.4531 1.500 0.7877 0.01509 0.00624 -0.1213 0.4428 0.4640 1.750 0.8137 0.01529 0.00639 -0.1207 0.4377 0.4760 2.000 0.8391 0.01544 0.00660 -0.1200 0.4323 0.4857 2.250 0.8645 0.01563 0.00674 -0.1193 0.4271 0.4950 2.500 0.8896 0.01583 0.00688 -0.1185 0.4222 0.5015 2.750 0.9150 0.01597 0.00705 -0.1179 0.4172 0.5064 3.000 0.9402 0.01612 0.00720 -0.1172 0.4119 0.5112 3.250 0.9649 0.01630 0.00733 -0.1164 0.4063 0.5166 3.500 0.9892 0.01653 0.00747 -0.1157 0.4012 0.5219 3.750 1.0138 0.01664 0.00767 -0.1149 0.3956 0.5266 4.000 1.0380 0.01681 0.00785 -0.1141 0.3900 0.5318 4.250 1.0618 0.01702 0.00802 -0.1132 0.3850 0.5376 4.500 1.0857 0.01724 0.00822 -0.1124 0.3805 0.5429 4.750 1.1096 0.01740 0.00845 -0.1116 0.3754 0.5484 5.000 1.1329 0.01759 0.00867 -0.1106 0.3703 0.5550 5.250 1.1555 0.01783 0.00888 -0.1096 0.3657 0.5619 5.500 1.1778 0.01806 0.00912 -0.1085 0.3616 0.5688 5.750 1.2004 0.01825 0.00939 -0.1075 0.3567 0.5767 6.000 1.2222 0.01847 0.00965 -0.1064 0.3516 0.5837 6.250 1.2435 0.01872 0.00990 -0.1052 0.3466 0.5915 6.500 1.2651 0.01899 0.01019 -0.1041 0.3420 0.6000 6.750 1.2864 0.01921 0.01050 -0.1030 0.3366 0.6090 7.000 1.3063 0.01947 0.01080 -0.1016 0.3316 0.6190 7.250 1.3255 0.01978 0.01111 -0.1001 0.3271 0.6315 7.500 1.3460 0.02005 0.01150 -0.0990 0.3223 0.6477 7.750 1.3659 0.02032 0.01191 -0.0977 0.3170 0.6731 8.000 1.3957 0.02037 0.01233 -0.0986 0.3112 1.0000 8.250 1.4126 0.02080 0.01276 -0.0969 0.3062 1.0000 8.500 1.4294 0.02123 0.01322 -0.0952 0.3006 1.0000 8.750 1.4445 0.02173 0.01371 -0.0934 0.2953 1.0000 9.000 1.4592 0.02227 0.01423 -0.0915 0.2905 1.0000 9.250 1.4748 0.02280 0.01480 -0.0899 0.2847 1.0000 9.500 1.4879 0.02342 0.01543 -0.0879 0.2791 1.0000 9.750 1.5000 0.02411 0.01610 -0.0860 0.2739 1.0000 10.000 1.5134 0.02479 0.01683 -0.0843 0.2677 1.0000 10.250 1.5241 0.02560 0.01764 -0.0823 0.2620 1.0000 10.500 1.5346 0.02648 0.01852 -0.0805 0.2569 1.0000 10.750 1.5459 0.02735 0.01945 -0.0788 0.2509 1.0000 11.000 1.5547 0.02840 0.02050 -0.0770 0.2458 1.0000 11.250 1.5634 0.02950 0.02161 -0.0753 0.2411 1.0000 11.500 1.5732 0.03060 0.02279 -0.0739 0.2358 1.0000 11.750 1.5809 0.03187 0.02408 -0.0724 0.2313 1.0000 12.000 1.5864 0.03333 0.02552 -0.0708 0.2272 1.0000 12.250 1.5955 0.03463 0.02692 -0.0696 0.2228 1.0000 12.500 1.6013 0.03620 0.02855 -0.0684 0.2179 1.0000 12.750 1.6053 0.03796 0.03032 -0.0672 0.2139 1.0000 13.000 1.6102 0.03973 0.03214 -0.0661 0.2097 1.0000 13.250 1.6151 0.04156 0.03405 -0.0652 0.2053 1.0000 13.500 1.6168 0.04372 0.03625 -0.0643 0.2008 1.0000 13.750 1.6174 0.04603 0.03858 -0.0635 0.1970 1.0000 14.000 1.6218 0.04811 0.04077 -0.0630 0.1934 1.0000 14.250 1.6243 0.05041 0.04315 -0.0624 0.1898 1.0000 14.500 1.6250 0.05293 0.04572 -0.0620 0.1864 1.0000 14.750 1.6242 0.05565 0.04845 -0.0616 0.1833 1.0000 15.000 1.6261 0.05820 0.05112 -0.0614 0.1802 1.0000 15.250 1.6262 0.06099 0.05402 -0.0613 0.1767 1.0000 15.500 1.6244 0.06406 0.05716 -0.0613 0.1733 1.0000 15.750 1.6210 0.06732 0.06044 -0.0614 0.1700 1.0000 16.000 1.6192 0.07053 0.06377 -0.0617 0.1667 1.0000 16.250 1.6162 0.07397 0.06732 -0.0620 0.1630 1.0000 16.500 1.6109 0.07773 0.07115 -0.0626 0.1592 1.0000 16.750 1.6051 0.08156 0.07501 -0.0632 0.1557 1.0000 17.000 1.5997 0.08555 0.07916 -0.0640 0.1517 1.0000 17.250 1.5924 0.08980 0.08350 -0.0649 0.1475 1.0000 17.500 1.5850 0.09404 0.08776 -0.0659 0.1437 1.0000 17.750 1.5770 0.09859 0.09246 -0.0672 0.1393 1.0000 18.000 1.5671 0.10340 0.09735 -0.0686 0.1346 1.0000 18.250 1.5581 0.10812 0.10214 -0.0701 0.1301 1.0000 18.500 1.5469 0.11329 0.10741 -0.0719 0.1246 1.0000 18.750 1.5359 0.11843 0.11260 -0.0737 0.1196 1.0000 19.000 1.5241 0.12377 0.11803 -0.0758 0.1138 1.0000 19.250 1.5127 0.12908 0.12338 -0.0780 0.1086 1.0000