XFOIL Version 6.96 Calculated polar for: S8036 (16%) 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 ------ -------- --------- --------- -------- -------- -------- -18.750 -0.8925 0.10832 0.10539 -0.0426 1.0000 0.0059 -18.500 -0.9260 0.09845 0.09537 -0.0477 1.0000 0.0059 -18.250 -0.9552 0.08948 0.08625 -0.0523 1.0000 0.0060 -18.000 -0.9777 0.08190 0.07853 -0.0562 1.0000 0.0059 -17.750 -1.0091 0.07317 0.06963 -0.0608 1.0000 0.0060 -17.500 -1.0211 0.06780 0.06414 -0.0634 1.0000 0.0060 -17.250 -1.0399 0.06174 0.05796 -0.0663 1.0000 0.0058 -17.000 -1.0454 0.05780 0.05391 -0.0679 1.0000 0.0060 -16.750 -1.0598 0.05295 0.04893 -0.0697 1.0000 0.0059 -16.500 -1.0656 0.04943 0.04531 -0.0707 1.0000 0.0059 -16.250 -1.0696 0.04634 0.04212 -0.0712 1.0000 0.0060 -16.000 -1.0766 0.04308 0.03876 -0.0716 1.0000 0.0059 -15.750 -1.0763 0.04071 0.03631 -0.0715 1.0000 0.0060 -15.500 -1.0776 0.03830 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0.00143 -0.0293 0.5785 0.6135 -0.250 0.1506 0.00658 0.00143 -0.0288 0.5729 0.6237 0.000 0.1774 0.00659 0.00143 -0.0285 0.5676 0.6318 0.250 0.2035 0.00659 0.00144 -0.0281 0.5612 0.6398 0.500 0.2296 0.00664 0.00145 -0.0277 0.5544 0.6464 0.750 0.2563 0.00664 0.00146 -0.0274 0.5480 0.6522 1.000 0.2823 0.00667 0.00148 -0.0270 0.5407 0.6585 1.250 0.3088 0.00671 0.00150 -0.0267 0.5340 0.6644 1.500 0.3345 0.00674 0.00152 -0.0262 0.5252 0.6704 1.750 0.3601 0.00678 0.00155 -0.0257 0.5159 0.6776 2.000 0.3852 0.00686 0.00159 -0.0252 0.5039 0.6838 2.250 0.4099 0.00692 0.00163 -0.0245 0.4909 0.6901 2.500 0.4349 0.00699 0.00168 -0.0239 0.4781 0.6966 2.750 0.4598 0.00708 0.00174 -0.0233 0.4670 0.7022 3.000 0.4837 0.00717 0.00181 -0.0225 0.4542 0.7089 3.500 0.5313 0.00738 0.00197 -0.0209 0.4257 0.7227 3.750 0.5547 0.00750 0.00206 -0.0200 0.4108 0.7305 4.000 0.5760 0.00769 0.00218 -0.0188 0.3883 0.7385 4.250 0.5966 0.00789 0.00231 -0.0174 0.3654 0.7474 4.500 0.6158 0.00815 0.00248 -0.0158 0.3390 0.7563 4.750 0.6352 0.00837 0.00264 -0.0141 0.3159 0.7666 5.000 0.6545 0.00858 0.00281 -0.0125 0.2964 0.7770 5.500 0.6920 0.00899 0.00316 -0.0090 0.2617 0.8019 5.750 0.7089 0.00918 0.00333 -0.0069 0.2459 0.8161 6.000 0.7237 0.00936 0.00351 -0.0044 0.2295 0.8338 6.250 0.7388 0.00955 0.00371 -0.0019 0.2151 0.8556 6.500 0.7555 0.00975 0.00396 0.0002 0.2000 0.8855 6.750 0.7900 0.01006 0.00430 -0.0017 0.1842 0.9186 7.000 0.8443 0.01053 0.00474 -0.0081 0.1675 0.9361 7.250 0.8996 0.01105 0.00518 -0.0147 0.1505 0.9453 7.500 0.9471 0.01153 0.00561 -0.0195 0.1387 0.9557 7.750 0.9745 0.01191 0.00595 -0.0199 0.1299 0.9743 8.000 0.9912 0.01221 0.00623 -0.0180 0.1236 0.9872 8.250 1.0148 0.01258 0.00657 -0.0176 0.1165 0.9928 8.500 1.0432 0.01293 0.00690 -0.0183 0.1103 0.9961 8.750 1.0722 0.01335 0.00728 -0.0193 0.1029 0.9986 9.000 1.0991 0.01372 0.00764 -0.0197 0.0969 1.0000 9.250 1.1086 0.01407 0.00797 -0.0166 0.0922 1.0000 9.500 1.1189 0.01443 0.00832 -0.0136 0.0881 1.0000 9.750 1.1312 0.01477 0.00868 -0.0111 0.0855 1.0000 10.000 1.1424 0.01518 0.00909 -0.0085 0.0820 1.0000 10.250 1.1530 0.01566 0.00956 -0.0059 0.0784 1.0000 10.500 1.1659 0.01610 0.01002 -0.0038 0.0764 1.0000 10.750 1.1786 0.01657 0.01052 -0.0017 0.0743 1.0000 11.000 1.1905 0.01712 0.01108 0.0003 0.0720 1.0000 11.250 1.2018 0.01775 0.01171 0.0024 0.0697 1.0000 11.500 1.2137 0.01839 0.01237 0.0042 0.0674 1.0000 11.750 1.2265 0.01901 0.01303 0.0058 0.0656 1.0000 12.000 1.2388 0.01971 0.01376 0.0074 0.0638 1.0000 12.250 1.2499 0.02052 0.01458 0.0090 0.0617 1.0000 12.500 1.2609 0.02137 0.01545 0.0105 0.0599 1.0000 12.750 1.2723 0.02223 0.01634 0.0118 0.0583 1.0000 13.000 1.2846 0.02308 0.01724 0.0130 0.0571 1.0000 13.250 1.2956 0.02405 0.01823 0.0142 0.0547 1.0000 13.500 1.3051 0.02513 0.01933 0.0154 0.0526 1.0000 13.750 1.3145 0.02627 0.02049 0.0166 0.0509 1.0000 14.000 1.3253 0.02733 0.02160 0.0176 0.0496 1.0000 14.250 1.3355 0.02848 0.02279 0.0185 0.0485 1.0000 14.500 1.3437 0.02978 0.02411 0.0195 0.0461 1.0000 14.750 1.3507 0.03121 0.02556 0.0205 0.0442 1.0000 15.000 1.3589 0.03257 0.02697 0.0213 0.0428 1.0000 15.250 1.3671 0.03398 0.02842 0.0220 0.0414 1.0000 15.500 1.3732 0.03557 0.03004 0.0228 0.0393 1.0000 15.750 1.3776 0.03736 0.03185 0.0235 0.0374 1.0000 16.000 1.3847 0.03897 0.03352 0.0240 0.0370 1.0000 16.250 1.3905 0.04071 0.03530 0.0245 0.0352 1.0000 16.500 1.3957 0.04255 0.03719 0.0250 0.0343 1.0000 16.750 1.3984 0.04466 0.03934 0.0254 0.0328 1.0000 17.000 1.4018 0.04677 0.04149 0.0257 0.0320 1.0000 17.250 1.4063 0.04881 0.04359 0.0259 0.0310 1.0000 17.500 1.4083 0.05114 0.04597 0.0260 0.0294 1.0000 17.750 1.4109 0.05344 0.04834 0.0260 0.0290 1.0000 18.000 1.4113 0.05602 0.05097 0.0260 0.0279 1.0000 18.250 1.4111 0.05871 0.05371 0.0259 0.0268 1.0000 18.500 1.4117 0.06139 0.05645 0.0256 0.0260 1.0000 18.750 1.4120 0.06414 0.05928 0.0253 0.0256 1.0000 19.000 1.4102 0.06715 0.06235 0.0249 0.0247 1.0000 19.250 1.4063 0.07048 0.06575 0.0243 0.0239 1.0000