XFOIL Version 6.96 Calculated polar for: AH 93-W-174 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 ------ -------- --------- --------- -------- -------- -------- -18.250 -0.9198 0.09139 0.08855 -0.0536 1.0000 0.0198 -18.000 -0.9433 0.08394 0.08099 -0.0580 1.0000 0.0199 -17.750 -0.9668 0.07662 0.07356 -0.0623 1.0000 0.0199 -17.500 -0.9886 0.06965 0.06647 -0.0665 1.0000 0.0201 -17.250 -1.0099 0.06291 0.05962 -0.0706 1.0000 0.0201 -17.000 -1.0264 0.05697 0.05356 -0.0743 1.0000 0.0202 -16.750 -1.0396 0.05169 0.04815 -0.0775 1.0000 0.0204 -16.500 -1.0482 0.04717 0.04352 -0.0803 1.0000 0.0205 -16.250 -1.0530 0.04336 0.03961 -0.0825 1.0000 0.0207 -16.000 -1.0556 0.04000 0.03615 -0.0843 1.0000 0.0209 -15.750 -1.0545 0.03724 0.03329 -0.0855 1.0000 0.0210 -15.500 -1.0510 0.03489 0.03085 -0.0864 1.0000 0.0212 -15.250 -1.0610 0.03145 0.02732 -0.0873 1.0000 0.0215 -15.000 -1.0634 0.02901 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-0.0895 0.5184 0.5471 -0.500 0.3830 0.00743 0.00209 -0.0897 0.5163 0.5766 -0.250 0.4117 0.00743 0.00211 -0.0898 0.5140 0.6020 0.000 0.4402 0.00747 0.00218 -0.0899 0.5111 0.6246 0.250 0.4692 0.00744 0.00221 -0.0901 0.5097 0.6443 0.500 0.4983 0.00743 0.00225 -0.0903 0.5081 0.6602 0.750 0.5273 0.00744 0.00229 -0.0905 0.5062 0.6747 1.000 0.5564 0.00746 0.00232 -0.0907 0.5042 0.6885 1.250 0.5852 0.00747 0.00236 -0.0909 0.5021 0.7016 1.500 0.6139 0.00750 0.00241 -0.0910 0.4999 0.7131 1.750 0.6425 0.00758 0.00247 -0.0912 0.4977 0.7244 2.000 0.6708 0.00769 0.00258 -0.0913 0.4950 0.7350 2.250 0.6997 0.00771 0.00264 -0.0915 0.4936 0.7448 2.500 0.7285 0.00773 0.00270 -0.0916 0.4918 0.7549 2.750 0.7571 0.00776 0.00277 -0.0917 0.4897 0.7647 3.000 0.7857 0.00781 0.00284 -0.0919 0.4877 0.7745 3.250 0.8140 0.00785 0.00291 -0.0920 0.4856 0.7825 3.500 0.8423 0.00792 0.00299 -0.0921 0.4834 0.7905 3.750 0.8704 0.00802 0.00308 -0.0921 0.4808 0.7974 4.000 0.8983 0.00812 0.00320 -0.0922 0.4784 0.8044 4.250 0.9270 0.00817 0.00328 -0.0924 0.4768 0.8113 4.500 0.9549 0.00820 0.00336 -0.0924 0.4747 0.8179 4.750 0.9831 0.00825 0.00345 -0.0925 0.4724 0.8248 5.000 1.0112 0.00831 0.00353 -0.0926 0.4701 0.8310 5.250 1.0386 0.00838 0.00363 -0.0926 0.4677 0.8373 5.500 1.0660 0.00850 0.00374 -0.0926 0.4648 0.8440 5.750 1.0933 0.00860 0.00388 -0.0925 0.4622 0.8501 6.000 1.1208 0.00863 0.00397 -0.0925 0.4597 0.8568 6.250 1.1485 0.00868 0.00405 -0.0926 0.4564 0.8633 6.500 1.1749 0.00872 0.00414 -0.0923 0.4528 0.8699 6.750 1.2011 0.00885 0.00426 -0.0921 0.4487 0.8771 7.000 1.2275 0.00891 0.00438 -0.0919 0.4451 0.8839 7.250 1.2541 0.00895 0.00449 -0.0918 0.4413 0.8913 7.500 1.2799 0.00903 0.00459 -0.0915 0.4368 0.8988 7.750 1.3039 0.00916 0.00473 -0.0909 0.4312 0.9075 8.000 1.3296 0.00919 0.00484 -0.0905 0.4259 0.9161 8.500 1.3755 0.00938 0.00509 -0.0888 0.4127 0.9409 8.750 1.3994 0.00944 0.00522 -0.0882 0.4060 0.9656 9.000 1.4289 0.00963 0.00541 -0.0889 0.3967 1.0000 9.250 1.4525 0.00990 0.00564 -0.0885 0.3841 1.0000 9.750 1.4953 0.01060 0.00624 -0.0869 0.3552 1.0000 10.000 1.5134 0.01104 0.00662 -0.0855 0.3371 1.0000 10.250 1.5268 0.01164 0.00713 -0.0834 0.3146 1.0000 10.500 1.5316 0.01238 0.00774 -0.0798 0.2910 1.0000 10.750 1.5307 0.01325 0.00850 -0.0753 0.2669 1.0000 11.000 1.5263 0.01428 0.00942 -0.0706 0.2443 1.0000 11.250 1.5185 0.01556 0.01060 -0.0659 0.2235 1.0000 11.500 1.5087 0.01716 0.01214 -0.0616 0.2060 1.0000 11.750 1.4984 0.01916 0.01409 -0.0582 0.1899 1.0000 12.000 1.4888 0.02148 0.01637 -0.0555 0.1747 1.0000 12.250 1.4777 0.02417 0.01902 -0.0531 0.1590 1.0000 12.750 1.4602 0.02968 0.02448 -0.0496 0.1349 1.0000 13.000 1.4490 0.03276 0.02753 -0.0480 0.1221 1.0000 13.250 1.4432 0.03547 0.03024 -0.0468 0.1131 1.0000 13.500 1.4350 0.03845 0.03320 -0.0456 0.1037 1.0000 13.750 1.4261 0.04159 0.03631 -0.0446 0.0938 1.0000 14.000 1.4211 0.04450 0.03921 -0.0439 0.0853 1.0000 14.250 1.4179 0.04734 0.04205 -0.0433 0.0777 1.0000 14.500 1.4140 0.05034 0.04504 -0.0429 0.0708 1.0000 14.750 1.4111 0.05330 0.04798 -0.0426 0.0639 1.0000 15.000 1.4104 0.05613 0.05083 -0.0424 0.0579 1.0000 15.250 1.4094 0.05904 0.05374 -0.0423 0.0526 1.0000 15.500 1.4079 0.06205 0.05673 -0.0422 0.0474 1.0000 15.750 1.4091 0.06484 0.05954 -0.0423 0.0433 1.0000 16.000 1.4089 0.06784 0.06255 -0.0425 0.0394 1.0000 16.250 1.4097 0.07076 0.06548 -0.0427 0.0357 1.0000 16.500 1.4105 0.07375 0.06849 -0.0430 0.0324 1.0000 16.750 1.4109 0.07683 0.07157 -0.0434 0.0294 1.0000 17.000 1.4126 0.07981 0.07460 -0.0439 0.0270 1.0000 17.250 1.4130 0.08297 0.07777 -0.0444 0.0245 1.0000 17.500 1.4147 0.08604 0.08089 -0.0450 0.0229 1.0000 17.750 1.4154 0.08925 0.08411 -0.0456 0.0212 1.0000 18.000 1.4167 0.09247 0.08738 -0.0464 0.0201 1.0000 18.250 1.4190 0.09555 0.09051 -0.0472 0.0189 1.0000 18.500 1.4194 0.09893 0.09393 -0.0481 0.0179 1.0000