XFOIL Version 6.96 Calculated polar for: SPICA 11.73% smoothed 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 ------ -------- --------- --------- -------- -------- -------- -10.000 -0.1677 0.08464 0.08201 -0.0800 0.7872 0.0138 -9.750 -0.1655 0.08179 0.07907 -0.0808 0.7654 0.0138 -9.500 -0.1627 0.07906 0.07628 -0.0817 0.7474 0.0139 -9.250 -0.1608 0.07621 0.07338 -0.0826 0.7318 0.0141 -9.000 -0.1601 0.07323 0.07036 -0.0836 0.7175 0.0142 -8.750 -0.1603 0.07024 0.06733 -0.0846 0.7049 0.0146 -8.500 -0.1657 0.06667 0.06375 -0.0859 0.6927 0.0148 -8.250 -0.1784 0.06307 0.06015 -0.0871 0.6827 0.0149 -8.000 -0.1957 0.05730 0.05433 -0.0909 0.6731 0.0155 -7.750 -0.2115 0.04920 0.04611 -0.0952 0.6663 0.0158 -7.500 -0.2487 0.03402 0.03042 -0.0974 0.6618 0.0164 -7.250 -0.2354 0.03135 0.02757 -0.0968 0.6539 0.0166 -7.000 -0.2193 0.02910 0.02514 -0.0961 0.6460 0.0168 -6.750 -0.2292 0.01944 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1.0000 3.250 0.8662 0.00717 0.00219 -0.0904 0.3984 1.0000 3.500 0.8893 0.00731 0.00228 -0.0894 0.3884 1.0000 3.750 0.9129 0.00744 0.00237 -0.0885 0.3796 1.0000 4.000 0.9358 0.00761 0.00249 -0.0876 0.3690 1.0000 4.250 0.9586 0.00780 0.00261 -0.0866 0.3566 1.0000 4.500 0.9817 0.00797 0.00273 -0.0856 0.3451 1.0000 4.750 1.0045 0.00816 0.00287 -0.0847 0.3339 1.0000 5.000 1.0269 0.00838 0.00302 -0.0837 0.3219 1.0000 5.250 1.0492 0.00861 0.00319 -0.0826 0.3095 1.0000 5.500 1.0719 0.00881 0.00336 -0.0817 0.2986 1.0000 5.750 1.0942 0.00904 0.00354 -0.0807 0.2873 1.0000 6.000 1.1163 0.00928 0.00373 -0.0796 0.2773 1.0000 6.250 1.1387 0.00950 0.00392 -0.0787 0.2678 1.0000 6.500 1.1608 0.00973 0.00412 -0.0777 0.2588 1.0000 7.000 1.2045 0.01022 0.00454 -0.0756 0.2415 1.0000 7.250 1.2255 0.01050 0.00479 -0.0744 0.2320 1.0000 7.500 1.2459 0.01082 0.00505 -0.0732 0.2211 1.0000 7.750 1.2661 0.01112 0.00532 -0.0719 0.2098 1.0000 8.000 1.2862 0.01143 0.00559 -0.0706 0.2004 1.0000 8.250 1.3051 0.01179 0.00590 -0.0692 0.1900 1.0000 8.500 1.3253 0.01207 0.00618 -0.0679 0.1819 1.0000 8.750 1.3440 0.01241 0.00649 -0.0665 0.1742 1.0000 9.000 1.3615 0.01279 0.00682 -0.0648 0.1640 1.0000 9.250 1.3776 0.01317 0.00718 -0.0629 0.1539 1.0000 9.500 1.3905 0.01359 0.00756 -0.0604 0.1438 1.0000 9.750 1.4004 0.01414 0.00804 -0.0574 0.1297 1.0000 10.000 1.4089 0.01479 0.00861 -0.0544 0.1144 1.0000 10.250 1.4178 0.01547 0.00923 -0.0515 0.1012 1.0000 10.500 1.4225 0.01639 0.01005 -0.0483 0.0843 1.0000 10.750 1.4271 0.01738 0.01096 -0.0452 0.0688 1.0000 11.000 1.4288 0.01862 0.01212 -0.0421 0.0528 1.0000 11.250 1.4210 0.02058 0.01393 -0.0384 0.0283 1.0000 11.500 1.4235 0.02210 0.01541 -0.0362 0.0189 1.0000 11.750 1.4311 0.02338 0.01672 -0.0347 0.0156 1.0000 12.000 1.4407 0.02458 0.01796 -0.0335 0.0141 1.0000 12.250 1.4497 0.02590 0.01932 -0.0324 0.0130 1.0000 12.500 1.4582 0.02731 0.02077 -0.0314 0.0121 1.0000 12.750 1.4666 0.02878 0.02230 -0.0306 0.0115 1.0000 13.000 1.4754 0.03027 0.02385 -0.0299 0.0111 1.0000 13.250 1.4828 0.03190 0.02554 -0.0292 0.0106 1.0000 13.500 1.4892 0.03367 0.02736 -0.0285 0.0102 1.0000 13.750 1.4944 0.03559 0.02934 -0.0279 0.0098 1.0000 14.000 1.4974 0.03775 0.03155 -0.0273 0.0093 1.0000 14.250 1.5006 0.03993 0.03380 -0.0268 0.0091 1.0000 14.500 1.5054 0.04198 0.03593 -0.0264 0.0088 1.0000 14.750 1.5094 0.04415 0.03816 -0.0261 0.0086 1.0000 15.000 1.5118 0.04652 0.04060 -0.0258 0.0084 1.0000 15.250 1.5129 0.04907 0.04323 -0.0256 0.0082 1.0000 15.500 1.5138 0.05172 0.04595 -0.0255 0.0079 1.0000 15.750 1.5135 0.05451 0.04881 -0.0254 0.0078 1.0000 16.000 1.5116 0.05756 0.05193 -0.0255 0.0075 1.0000 16.250 1.5097 0.06067 0.05512 -0.0256 0.0074 1.0000 16.500 1.5062 0.06402 0.05855 -0.0258 0.0073 1.0000 16.750 1.5027 0.06740 0.06201 -0.0261 0.0072 1.0000 17.000 1.4958 0.07130 0.06600 -0.0265 0.0070 1.0000 17.250 1.4892 0.07524 0.07003 -0.0271 0.0069 1.0000 17.500 1.4856 0.07883 0.07370 -0.0277 0.0068 1.0000 17.750 1.4788 0.08288 0.07785 -0.0284 0.0068 1.0000 18.000 1.4740 0.08672 0.08177 -0.0291 0.0066 1.0000 18.250 1.4670 0.09094 0.08608 -0.0301 0.0065 1.0000 18.500 1.4571 0.09565 0.09089 -0.0312 0.0065 1.0000 18.750 1.4511 0.09981 0.09514 -0.0323 0.0063 1.0000 19.000 1.4431 0.10435 0.09976 -0.0337 0.0062 1.0000 19.250 1.4327 0.10935 0.10487 -0.0352 0.0062 1.0000