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 = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -19.250 -1.1189 0.10123 0.09687 -0.0219 1.0000 0.0650 -19.000 -1.1200 0.09787 0.09348 -0.0231 1.0000 0.0663 -18.750 -1.1167 0.09512 0.09072 -0.0241 1.0000 0.0677 -18.500 -1.1129 0.09246 0.08802 -0.0250 1.0000 0.0693 -18.250 -1.1104 0.08962 0.08515 -0.0260 1.0000 0.0705 -18.000 -1.1079 0.08685 0.08236 -0.0269 1.0000 0.0722 -17.500 -1.1023 0.08160 0.07646 -0.0288 0.7804 0.0756 -17.250 -1.0965 0.07934 0.07408 -0.0295 0.7568 0.0772 -17.000 -1.0925 0.07684 0.07149 -0.0302 0.7386 0.0789 -16.750 -1.0917 0.07398 0.06856 -0.0310 0.7234 0.0810 -16.500 -1.0869 0.07159 0.06611 -0.0317 0.7107 0.0833 -16.250 -1.0826 0.06915 0.06358 -0.0324 0.6984 0.0854 -16.000 -1.0793 0.06665 0.06103 -0.0330 0.6887 0.0878 -15.750 -1.0752 0.06423 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-0.0984 0.4885 0.4276 -1.000 0.2346 0.00909 0.00311 -0.0993 0.4867 0.4316 -0.750 0.2667 0.00909 0.00311 -0.1002 0.4849 0.4353 -0.500 0.2989 0.00908 0.00311 -0.1011 0.4830 0.4390 -0.250 0.3311 0.00906 0.00311 -0.1019 0.4810 0.4431 0.000 0.3631 0.00907 0.00312 -0.1028 0.4787 0.4469 0.250 0.3949 0.00909 0.00313 -0.1036 0.4763 0.4509 0.500 0.4265 0.00912 0.00315 -0.1043 0.4737 0.4542 0.750 0.4582 0.00916 0.00318 -0.1051 0.4712 0.4579 1.000 0.4903 0.00915 0.00321 -0.1059 0.4700 0.4616 1.250 0.5222 0.00916 0.00324 -0.1067 0.4685 0.4654 1.500 0.5539 0.00918 0.00328 -0.1074 0.4666 0.4692 1.750 0.5855 0.00921 0.00331 -0.1081 0.4643 0.4723 2.000 0.6171 0.00924 0.00335 -0.1088 0.4620 0.4751 2.250 0.6486 0.00927 0.00340 -0.1095 0.4599 0.4785 2.500 0.6800 0.00931 0.00346 -0.1102 0.4575 0.4818 2.750 0.7111 0.00938 0.00352 -0.1108 0.4548 0.4853 3.000 0.7421 0.00945 0.00359 -0.1114 0.4520 0.4886 3.250 0.7734 0.00949 0.00365 -0.1120 0.4505 0.4912 3.500 0.8047 0.00953 0.00372 -0.1126 0.4486 0.4933 3.750 0.8360 0.00957 0.00379 -0.1133 0.4463 0.4964 4.000 0.8671 0.00962 0.00387 -0.1139 0.4436 0.4993 4.250 0.8980 0.00968 0.00395 -0.1144 0.4409 0.5024 4.500 0.9285 0.00977 0.00404 -0.1149 0.4379 0.5055 4.750 0.9589 0.00987 0.00414 -0.1153 0.4347 0.5081 5.000 0.9895 0.00995 0.00424 -0.1158 0.4322 0.5102 5.250 1.0202 0.01001 0.00432 -0.1163 0.4295 0.5118 5.500 1.0508 0.01008 0.00442 -0.1168 0.4259 0.5147 5.750 1.0809 0.01018 0.00454 -0.1172 0.4210 0.5178 6.000 1.1102 0.01033 0.00467 -0.1175 0.4152 0.5206 6.250 1.1405 0.01040 0.00479 -0.1179 0.4110 0.5232 6.500 1.1702 0.01052 0.00491 -0.1183 0.4054 0.5255 6.750 1.1987 0.01072 0.00508 -0.1184 0.3976 0.5279 7.000 1.2281 0.01084 0.00522 -0.1187 0.3906 0.5300 7.250 1.2562 0.01106 0.00540 -0.1187 0.3817 0.5315 7.500 1.2844 0.01125 0.00559 -0.1189 0.3719 0.5341 7.750 1.3107 0.01157 0.00586 -0.1187 0.3571 0.5366 8.000 1.3355 0.01198 0.00619 -0.1183 0.3380 0.5391 8.250 1.3589 0.01247 0.00659 -0.1177 0.3177 0.5417 8.500 1.3804 0.01305 0.00707 -0.1169 0.2961 0.5440 8.750 1.3975 0.01387 0.00773 -0.1154 0.2669 0.5459 9.000 1.4108 0.01482 0.00851 -0.1134 0.2372 0.5477 9.250 1.4213 0.01581 0.00935 -0.1110 0.2116 0.5493 9.500 1.4312 0.01670 0.01014 -0.1084 0.1924 0.5508 9.750 1.4323 0.01758 0.01098 -0.1044 0.1780 0.5525 10.000 1.4355 0.01873 0.01209 -0.1012 0.1641 0.5549 10.250 1.4379 0.02018 0.01352 -0.0987 0.1512 0.5569 10.500 1.4394 0.02206 0.01537 -0.0969 0.1395 0.5588 10.750 1.4409 0.02429 0.01761 -0.0958 0.1288 0.5609 11.000 1.4424 0.02672 0.02003 -0.0950 0.1195 0.5630 11.250 1.4436 0.02925 0.02257 -0.0943 0.1111 0.5649 11.500 1.4432 0.03194 0.02528 -0.0936 0.1037 0.5667 11.750 1.4404 0.03485 0.02819 -0.0927 0.0967 0.5681 12.000 1.4368 0.03782 0.03117 -0.0919 0.0902 0.5694 12.250 1.4345 0.04061 0.03398 -0.0910 0.0843 0.5706 12.500 1.4300 0.04365 0.03702 -0.0902 0.0787 0.5716 12.750 1.4249 0.04673 0.04012 -0.0893 0.0738 0.5730 13.000 1.4234 0.04949 0.04291 -0.0886 0.0690 0.5752 13.250 1.4212 0.05249 0.04594 -0.0881 0.0648 0.5771 13.500 1.4203 0.05536 0.04884 -0.0876 0.0608 0.5790 13.750 1.4205 0.05820 0.05171 -0.0872 0.0574 0.5806 14.000 1.4214 0.06097 0.05450 -0.0868 0.0539 0.5823 14.250 1.4216 0.06391 0.05747 -0.0865 0.0509 0.5838 14.500 1.4233 0.06663 0.06020 -0.0862 0.0480 0.5854 14.750 1.4236 0.06959 0.06319 -0.0860 0.0451 0.5869 15.000 1.4252 0.07242 0.06604 -0.0859 0.0426 0.5884 15.250 1.4275 0.07515 0.06879 -0.0857 0.0400 0.5898 15.500 1.4276 0.07820 0.07187 -0.0856 0.0380 0.5911 15.750 1.4301 0.08095 0.07464 -0.0855 0.0359 0.5923 16.000 1.4326 0.08374 0.07745 -0.0855 0.0341 0.5935 16.250 1.4339 0.08674 0.08051 -0.0856 0.0326 0.5956