XFOIL Version 6.96 Calculated polar for: WB-135/35 13.5% smoothed 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -11.000 -0.5255 0.06691 0.06329 -0.0744 1.0000 0.0358 -10.750 -0.5339 0.06248 0.05889 -0.0744 1.0000 0.0349 -10.500 -0.5598 0.05709 0.05350 -0.0760 1.0000 0.0337 -10.250 -0.5934 0.05417 0.05059 -0.0760 1.0000 0.0339 -10.000 -0.6295 0.05297 0.04943 -0.0705 1.0000 0.0330 -9.750 -0.6580 0.05145 0.04784 -0.0667 0.9991 0.0333 -9.500 -0.6486 0.04479 0.04065 -0.0742 0.9890 0.0331 -9.250 -0.6326 0.03947 0.03478 -0.0785 0.9814 0.0323 -9.000 -0.6137 0.03511 0.02986 -0.0808 0.9732 0.0317 -8.750 -0.5890 0.03180 0.02608 -0.0826 0.9667 0.0315 -8.500 -0.5611 0.02926 0.02319 -0.0840 0.9602 0.0318 -8.250 -0.5263 0.02704 0.02068 -0.0863 0.9568 0.0325 -8.000 -0.4994 0.02543 0.01886 -0.0867 0.9490 0.0337 -7.750 -0.4629 0.02417 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0.01402 0.00663 -0.0916 0.8256 0.3402 -2.750 0.1006 0.01382 0.00640 -0.0917 0.8209 0.3539 -2.500 0.1238 0.01371 0.00634 -0.0907 0.8123 0.3675 -2.250 0.1532 0.01348 0.00606 -0.0906 0.8058 0.3833 -2.000 0.1767 0.01337 0.00598 -0.0896 0.7966 0.3981 -1.750 0.2058 0.01320 0.00577 -0.0895 0.7907 0.4148 -1.500 0.2293 0.01315 0.00576 -0.0886 0.7824 0.4312 -1.250 0.2577 0.01301 0.00561 -0.0884 0.7763 0.4490 -1.000 0.2816 0.01295 0.00561 -0.0875 0.7680 0.4659 -0.750 0.3095 0.01282 0.00548 -0.0872 0.7616 0.4841 -0.500 0.3339 0.01279 0.00552 -0.0864 0.7544 0.5034 -0.250 0.3606 0.01273 0.00547 -0.0860 0.7483 0.5253 0.000 0.3865 0.01265 0.00546 -0.0854 0.7421 0.5471 0.250 0.4112 0.01257 0.00546 -0.0847 0.7350 0.5724 0.500 0.4386 0.01243 0.00538 -0.0843 0.7293 0.6013 0.750 0.4610 0.01230 0.00544 -0.0832 0.7217 0.6344 1.000 0.4874 0.01204 0.00536 -0.0826 0.7157 0.6824 1.250 0.5380 0.01146 0.00544 -0.0869 0.7073 0.8569 1.500 0.6348 0.01131 0.00525 -0.1013 0.6984 1.0000 1.750 0.6576 0.01139 0.00529 -0.1003 0.6894 1.0000 2.000 0.6823 0.01146 0.00528 -0.0995 0.6814 1.0000 2.250 0.7063 0.01151 0.00528 -0.0986 0.6721 1.0000 2.500 0.7293 0.01157 0.00532 -0.0975 0.6618 1.0000 2.750 0.7535 0.01161 0.00531 -0.0965 0.6515 1.0000 3.000 0.7771 0.01165 0.00529 -0.0955 0.6401 1.0000 3.250 0.7991 0.01171 0.00534 -0.0942 0.6269 1.0000 3.500 0.8213 0.01176 0.00538 -0.0928 0.6125 1.0000 3.750 0.8432 0.01182 0.00538 -0.0914 0.5959 1.0000 4.000 0.8636 0.01190 0.00543 -0.0897 0.5751 1.0000 4.250 0.8832 0.01202 0.00546 -0.0879 0.5507 1.0000 4.500 0.9010 0.01221 0.00555 -0.0857 0.5203 1.0000 4.750 0.9176 0.01252 0.00569 -0.0834 0.4869 1.0000 5.000 0.9338 0.01295 0.00591 -0.0811 0.4580 1.0000 5.250 0.9509 0.01341 0.00621 -0.0791 0.4353 1.0000 5.500 0.9692 0.01389 0.00657 -0.0774 0.4183 1.0000 5.750 0.9886 0.01435 0.00694 -0.0759 0.4046 1.0000 6.000 1.0085 0.01480 0.00734 -0.0745 0.3924 1.0000 6.250 1.0280 0.01526 0.00774 -0.0730 0.3803 1.0000 6.500 1.0465 0.01572 0.00814 -0.0714 0.3675 1.0000 6.750 1.0646 0.01619 0.00854 -0.0697 0.3550 1.0000 7.000 1.0832 0.01657 0.00895 -0.0681 0.3445 1.0000 7.250 1.1027 0.01699 0.00939 -0.0667 0.3358 1.0000 7.500 1.1211 0.01746 0.00982 -0.0652 0.3263 1.0000 7.750 1.1349 0.01778 0.01020 -0.0628 0.3137 1.0000 8.000 1.1509 0.01815 0.01063 -0.0608 0.3039 1.0000 8.250 1.1646 0.01857 0.01105 -0.0584 0.2940 1.0000 8.500 1.1760 0.01892 0.01146 -0.0556 0.2836 1.0000 8.750 1.1840 0.01931 0.01190 -0.0523 0.2690 1.0000 9.000 1.1932 0.01977 0.01238 -0.0493 0.2536 1.0000 9.250 1.2021 0.02030 0.01294 -0.0465 0.2325 1.0000 9.500 1.2070 0.02114 0.01365 -0.0434 0.1966 1.0000 9.750 1.2026 0.02273 0.01487 -0.0396 0.1438 1.0000 10.000 1.1797 0.02587 0.01733 -0.0344 0.0592 1.0000 10.250 1.1762 0.02791 0.01923 -0.0315 0.0394 1.0000 10.500 1.1811 0.02944 0.02082 -0.0295 0.0346 1.0000 10.750 1.1840 0.03118 0.02263 -0.0275 0.0312 1.0000 11.000 1.1859 0.03306 0.02462 -0.0256 0.0294 1.0000 11.250 1.1896 0.03487 0.02657 -0.0241 0.0282 1.0000 11.500 1.1916 0.03688 0.02873 -0.0226 0.0275 1.0000 11.750 1.1915 0.03915 0.03113 -0.0213 0.0267 1.0000 12.000 1.1905 0.04158 0.03369 -0.0202 0.0263 1.0000 12.250 1.1865 0.04441 0.03663 -0.0192 0.0257 1.0000 12.500 1.1820 0.04738 0.03971 -0.0184 0.0253 1.0000 12.750 1.1790 0.05031 0.04274 -0.0178 0.0251 1.0000 13.000 1.1747 0.05346 0.04599 -0.0173 0.0249 1.0000 13.250 1.1702 0.05673 0.04933 -0.0169 0.0245 1.0000 13.500 1.1665 0.05994 0.05260 -0.0165 0.0241 1.0000 13.750 1.1643 0.06294 0.05565 -0.0158 0.0237 1.0000 14.000 1.1666 0.06529 0.05800 -0.0146 0.0230 1.0000 14.250 1.1720 0.06760 0.06041 -0.0143 0.0227 1.0000 14.500 1.1789 0.06970 0.06260 -0.0136 0.0224 1.0000 14.750 1.1866 0.07174 0.06472 -0.0129 0.0221 1.0000 15.000 1.1968 0.07349 0.06656 -0.0119 0.0219 1.0000 15.250 1.2070 0.07538 0.06855 -0.0110 0.0218 1.0000 15.500 1.2166 0.07746 0.07076 -0.0100 0.0217 1.0000 15.750 1.2241 0.07991 0.07336 -0.0094 0.0218 1.0000 16.000 1.2298 0.08271 0.07635 -0.0089 0.0219 1.0000 16.250 1.2329 0.08591 0.07972 -0.0087 0.0221 1.0000 16.500 1.2335 0.08955 0.08354 -0.0088 0.0223 1.0000 16.750 1.2325 0.09354 0.08771 -0.0091 0.0226 1.0000 17.000 1.2312 0.09796 0.09231 -0.0093 0.0229 1.0000 17.250 1.2323 0.10206 0.09658 -0.0097 0.0232 1.0000 17.500 1.2232 0.10610 0.10078 -0.0118 0.0235 1.0000 17.750 1.2091 0.11158 0.10647 -0.0145 0.0237 1.0000 18.000 1.1941 0.11764 0.11272 -0.0175 0.0237 1.0000 18.250 1.1724 0.12516 0.12054 -0.0222 0.0243 1.0000 18.500 1.1269 0.13840 0.13421 -0.0312 0.0253 1.0000 18.750 1.0918 0.15066 0.14675 -0.0393 0.0262 1.0000