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 = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -18.500 -0.9325 0.09413 0.09120 -0.0518 1.0000 0.0158 -18.250 -0.9842 0.08222 0.07910 -0.0588 1.0000 0.0158 -18.000 -1.0316 0.07122 0.06791 -0.0655 1.0000 0.0157 -17.750 -1.0673 0.06220 0.05872 -0.0710 1.0000 0.0157 -17.500 -1.0940 0.05474 0.05110 -0.0758 1.0000 0.0158 -17.250 -1.1114 0.04889 0.04512 -0.0795 1.0000 0.0158 -17.000 -1.1219 0.04429 0.04040 -0.0822 1.0000 0.0159 -16.750 -1.1180 0.04021 0.03622 -0.0865 0.9983 0.0162 -16.500 -1.0327 0.03566 0.03139 -0.1062 0.9063 0.0169 -16.250 -0.9979 0.03321 0.02842 -0.1137 0.8011 0.0172 -16.000 -0.9953 0.03128 0.02629 -0.1139 0.7673 0.0174 -15.750 -0.9913 0.02956 0.02441 -0.1139 0.7433 0.0176 -15.500 -0.9868 0.02801 0.02272 -0.1136 0.7225 0.0180 -15.250 -0.9832 0.02646 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-0.0889 0.4940 0.3089 -0.750 0.3561 0.00810 0.00183 -0.0892 0.4925 0.3446 -0.500 0.3847 0.00797 0.00181 -0.0894 0.4908 0.3825 -0.250 0.4134 0.00784 0.00181 -0.0897 0.4887 0.4230 0.000 0.4420 0.00773 0.00181 -0.0899 0.4866 0.4633 0.250 0.4705 0.00764 0.00182 -0.0901 0.4843 0.5003 0.500 0.4991 0.00760 0.00184 -0.0903 0.4822 0.5292 0.750 0.5276 0.00757 0.00187 -0.0904 0.4801 0.5557 1.000 0.5564 0.00756 0.00191 -0.0906 0.4783 0.5800 1.250 0.5853 0.00753 0.00196 -0.0909 0.4766 0.6021 1.500 0.6142 0.00752 0.00200 -0.0911 0.4746 0.6215 1.750 0.6430 0.00753 0.00205 -0.0913 0.4724 0.6396 2.000 0.6718 0.00754 0.00211 -0.0915 0.4704 0.6560 2.250 0.7004 0.00758 0.00217 -0.0916 0.4683 0.6708 2.500 0.7288 0.00761 0.00224 -0.0917 0.4660 0.6856 2.750 0.7569 0.00767 0.00232 -0.0918 0.4636 0.7006 3.000 0.7855 0.00770 0.00240 -0.0920 0.4618 0.7135 3.250 0.8143 0.00774 0.00247 -0.0922 0.4600 0.7241 3.500 0.8428 0.00778 0.00255 -0.0923 0.4578 0.7336 3.750 0.8713 0.00784 0.00263 -0.0925 0.4554 0.7416 4.000 0.8994 0.00790 0.00271 -0.0926 0.4530 0.7492 4.250 0.9275 0.00798 0.00280 -0.0927 0.4506 0.7570 4.500 0.9551 0.00806 0.00290 -0.0927 0.4480 0.7643 4.750 0.9833 0.00813 0.00300 -0.0928 0.4460 0.7715 5.000 1.0117 0.00819 0.00310 -0.0929 0.4438 0.7778 5.250 1.0396 0.00825 0.00321 -0.0930 0.4412 0.7843 5.500 1.0674 0.00834 0.00331 -0.0931 0.4383 0.7910 5.750 1.0948 0.00843 0.00343 -0.0931 0.4354 0.7969 6.000 1.1214 0.00855 0.00356 -0.0930 0.4317 0.8035 6.250 1.1493 0.00862 0.00367 -0.0931 0.4279 0.8099 6.500 1.1763 0.00871 0.00380 -0.0930 0.4229 0.8159 6.750 1.2023 0.00885 0.00394 -0.0928 0.4175 0.8224 7.000 1.2293 0.00896 0.00408 -0.0927 0.4123 0.8287 7.250 1.2553 0.00908 0.00424 -0.0925 0.4062 0.8348 7.500 1.2805 0.00925 0.00441 -0.0922 0.3994 0.8416 7.750 1.3055 0.00943 0.00459 -0.0918 0.3897 0.8479 8.000 1.3293 0.00964 0.00480 -0.0912 0.3788 0.8550 8.250 1.3515 0.00994 0.00506 -0.0904 0.3638 0.8624 8.500 1.3718 0.01028 0.00536 -0.0893 0.3473 0.8702 8.750 1.3914 0.01066 0.00571 -0.0881 0.3311 0.8789 9.000 1.4058 0.01120 0.00617 -0.0859 0.3086 0.8891 9.250 1.4121 0.01201 0.00683 -0.0825 0.2751 0.9024 9.500 1.4086 0.01286 0.00756 -0.0773 0.2430 0.9249 10.000 1.4047 0.01475 0.00928 -0.0684 0.1941 1.0000 10.250 1.4015 0.01588 0.01034 -0.0644 0.1769 1.0000 10.750 1.3877 0.01919 0.01354 -0.0574 0.1444 1.0000 11.000 1.3843 0.02111 0.01543 -0.0552 0.1326 1.0000 11.500 1.3770 0.02553 0.01981 -0.0516 0.1100 1.0000 11.750 1.3732 0.02792 0.02219 -0.0501 0.0999 1.0000 12.000 1.3699 0.03035 0.02461 -0.0488 0.0914 1.0000 12.250 1.3664 0.03283 0.02709 -0.0476 0.0839 1.0000 12.500 1.3654 0.03517 0.02944 -0.0465 0.0771 1.0000 12.750 1.3629 0.03765 0.03192 -0.0456 0.0709 1.0000 13.000 1.3589 0.04033 0.03459 -0.0446 0.0636 1.0000 13.250 1.3604 0.04263 0.03691 -0.0440 0.0593 1.0000 13.500 1.3589 0.04527 0.03955 -0.0434 0.0539 1.0000 13.750 1.3593 0.04780 0.04208 -0.0430 0.0482 1.0000 14.000 1.3606 0.05032 0.04462 -0.0427 0.0446 1.0000 14.250 1.3626 0.05279 0.04710 -0.0424 0.0408 1.0000 14.500 1.3646 0.05535 0.04968 -0.0422 0.0374 1.0000 15.000 1.3701 0.06042 0.05478 -0.0421 0.0316 1.0000 15.500 1.3764 0.06556 0.05997 -0.0423 0.0268 1.0000 15.750 1.3798 0.06817 0.06260 -0.0424 0.0248 1.0000 16.000 1.3835 0.07077 0.06523 -0.0427 0.0229 1.0000 16.250 1.3861 0.07355 0.06804 -0.0430 0.0210 1.0000 16.500 1.3903 0.07616 0.07068 -0.0433 0.0195 1.0000 16.750 1.3929 0.07904 0.07359 -0.0437 0.0181 1.0000 17.000 1.3967 0.08178 0.07637 -0.0442 0.0170 1.0000 17.250 1.4001 0.08460 0.07923 -0.0447 0.0160 1.0000 17.500 1.4032 0.08749 0.08216 -0.0453 0.0152 1.0000 17.750 1.4064 0.09040 0.08510 -0.0460 0.0142 1.0000 18.000 1.4095 0.09338 0.08814 -0.0467 0.0138 1.0000 18.250 1.4135 0.09625 0.09105 -0.0474 0.0131 1.0000 18.500 1.4162 0.09931 0.09416 -0.0483 0.0126 1.0000 18.750 1.4180 0.10253 0.09742 -0.0492 0.0120 1.0000 19.000 1.4210 0.10558 0.10052 -0.0501 0.0116 1.0000