XFOIL Version 6.96 Calculated polar for: AH 93-W-257 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 ------ -------- --------- --------- -------- -------- -------- -19.000 -1.1366 0.09585 0.09165 -0.0237 1.0000 0.0800 -18.750 -1.1361 0.09279 0.08858 -0.0248 1.0000 0.0818 -18.500 -1.1358 0.08972 0.08549 -0.0258 1.0000 0.0837 -18.250 -1.1297 0.08739 0.08312 -0.0266 1.0000 0.0854 -18.000 -1.1301 0.08427 0.07999 -0.0275 1.0000 0.0876 -17.750 -1.1319 0.08102 0.07672 -0.0285 1.0000 0.0900 -17.500 -1.1286 0.07842 0.07411 -0.0293 1.0000 0.0924 -17.250 -1.1251 0.07582 0.07147 -0.0300 1.0000 0.0945 -17.000 -1.1271 0.07266 0.06831 -0.0309 1.0000 0.0978 -16.750 -1.1260 0.06986 0.06551 -0.0316 1.0000 0.1009 -16.500 -1.1233 0.06727 0.06289 -0.0323 1.0000 0.1040 -16.250 -1.1247 0.06429 0.05992 -0.0329 1.0000 0.1082 -16.000 -1.1240 0.06152 0.05714 -0.0336 1.0000 0.1123 -15.750 -1.1241 0.05875 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0.00347 -0.0972 0.5189 0.4530 -1.500 0.1719 0.00919 0.00346 -0.0981 0.5164 0.4564 -1.250 0.2040 0.00920 0.00347 -0.0990 0.5133 0.4609 -1.000 0.2359 0.00926 0.00353 -0.0998 0.5105 0.4648 -0.750 0.2681 0.00925 0.00353 -0.1007 0.5095 0.4686 -0.500 0.3002 0.00925 0.00354 -0.1015 0.5081 0.4718 -0.250 0.3323 0.00925 0.00354 -0.1023 0.5063 0.4746 0.000 0.3644 0.00922 0.00355 -0.1032 0.5043 0.4789 0.250 0.3964 0.00923 0.00357 -0.1040 0.5022 0.4826 0.500 0.4282 0.00925 0.00360 -0.1047 0.5002 0.4862 0.750 0.4599 0.00929 0.00363 -0.1055 0.4981 0.4893 1.000 0.4915 0.00936 0.00366 -0.1062 0.4958 0.4918 1.250 0.5228 0.00942 0.00371 -0.1069 0.4929 0.4950 1.500 0.5543 0.00949 0.00380 -0.1076 0.4902 0.4989 1.750 0.5860 0.00950 0.00385 -0.1083 0.4889 0.5022 2.000 0.6176 0.00953 0.00391 -0.1090 0.4873 0.5052 2.250 0.6492 0.00956 0.00396 -0.1097 0.4855 0.5079 2.500 0.6807 0.00960 0.00400 -0.1103 0.4834 0.5102 2.750 0.7122 0.00965 0.00404 -0.1110 0.4812 0.5122 3.000 0.7434 0.00965 0.00409 -0.1116 0.4790 0.5163 3.250 0.7744 0.00972 0.00416 -0.1122 0.4766 0.5194 3.500 0.8052 0.00983 0.00427 -0.1127 0.4736 0.5221 3.750 0.8359 0.00995 0.00439 -0.1133 0.4707 0.5246 4.000 0.8671 0.00999 0.00446 -0.1138 0.4692 0.5270 4.250 0.8983 0.01003 0.00453 -0.1144 0.4673 0.5293 4.500 0.9293 0.01009 0.00460 -0.1150 0.4650 0.5311 4.750 0.9602 0.01011 0.00466 -0.1155 0.4626 0.5342 5.000 0.9909 0.01015 0.00474 -0.1160 0.4599 0.5373 5.250 1.0212 0.01024 0.00483 -0.1164 0.4568 0.5397 5.500 1.0509 0.01041 0.00498 -0.1168 0.4527 0.5420 5.750 1.0816 0.01045 0.00507 -0.1172 0.4501 0.5445 6.000 1.1122 0.01048 0.00515 -0.1177 0.4469 0.5469 6.250 1.1425 0.01054 0.00523 -0.1181 0.4433 0.5490 6.500 1.1724 0.01064 0.00532 -0.1184 0.4392 0.5506 6.750 1.2011 0.01082 0.00546 -0.1186 0.4335 0.5525 7.000 1.2317 0.01080 0.00553 -0.1191 0.4300 0.5560 7.250 1.2616 0.01087 0.00564 -0.1194 0.4253 0.5586 7.500 1.2903 0.01100 0.00577 -0.1196 0.4192 0.5609 7.750 1.3191 0.01114 0.00592 -0.1197 0.4126 0.5630 8.000 1.3480 0.01126 0.00606 -0.1199 0.4050 0.5652 8.250 1.3752 0.01150 0.00626 -0.1198 0.3972 0.5674 8.500 1.4040 0.01163 0.00642 -0.1200 0.3899 0.5695 8.750 1.4300 0.01192 0.00666 -0.1197 0.3790 0.5710 9.000 1.4570 0.01216 0.00688 -0.1196 0.3680 0.5721 9.250 1.4825 0.01242 0.00713 -0.1193 0.3568 0.5755 9.500 1.5061 0.01281 0.00749 -0.1187 0.3429 0.5782 9.750 1.5279 0.01329 0.00791 -0.1178 0.3263 0.5805 10.000 1.5476 0.01387 0.00842 -0.1166 0.3078 0.5826 10.250 1.5640 0.01457 0.00902 -0.1150 0.2871 0.5846 10.500 1.5752 0.01545 0.00979 -0.1126 0.2645 0.5865 10.750 1.5791 0.01648 0.01071 -0.1091 0.2435 0.5884 11.000 1.5743 0.01760 0.01177 -0.1042 0.2260 0.5901 11.250 1.5727 0.01911 0.01320 -0.1008 0.2086 0.5915 11.500 1.5688 0.02112 0.01517 -0.0981 0.1927 0.5926 11.750 1.5644 0.02366 0.01768 -0.0965 0.1780 0.5942 12.000 1.5597 0.02655 0.02056 -0.0954 0.1652 0.5969 12.250 1.5534 0.02971 0.02371 -0.0943 0.1537 0.5989 12.500 1.5459 0.03300 0.02701 -0.0933 0.1434 0.6007 12.750 1.5389 0.03624 0.03026 -0.0923 0.1342 0.6025 13.000 1.5299 0.03962 0.03365 -0.0912 0.1261 0.6041 13.250 1.5190 0.04319 0.03722 -0.0901 0.1183 0.6057 13.500 1.5106 0.04653 0.04058 -0.0891 0.1111 0.6073 13.750 1.5037 0.04979 0.04385 -0.0882 0.1044 0.6088 14.000 1.4960 0.05330 0.04735 -0.0875 0.0979 0.6101 14.250 1.4903 0.05667 0.05073 -0.0870 0.0916 0.6114 14.500 1.4872 0.05979 0.05386 -0.0865 0.0856 0.6126 14.750 1.4817 0.06327 0.05733 -0.0861 0.0802 0.6136 15.000 1.4786 0.06647 0.06052 -0.0857 0.0746 0.6145 15.250 1.4761 0.06969 0.06377 -0.0855 0.0697 0.6164 15.500 1.4744 0.07287 0.06697 -0.0853 0.0652 0.6188 15.750 1.4724 0.07607 0.07018 -0.0852 0.0608 0.6209 16.000 1.4711 0.07926 0.07340 -0.0851 0.0572 0.6228 16.250 1.4705 0.08233 0.07649 -0.0850 0.0537 0.6246 16.500 1.4693 0.08557 0.07975 -0.0850 0.0505 0.6263 16.750 1.4688 0.08870 0.08291 -0.0851 0.0477 0.6279 17.000 1.4697 0.09167 0.08589 -0.0851 0.0449 0.6295