XFOIL Version 6.96 Calculated polar for: LWK 80-100 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -11.750 -0.7135 0.09312 0.09094 -0.0086 1.0000 0.0155 -11.500 -0.7303 0.08654 0.08440 -0.0128 1.0000 0.0145 -11.250 -0.7737 0.06822 0.06593 -0.0274 1.0000 0.0138 -11.000 -0.8100 0.05945 0.05697 -0.0323 1.0000 0.0133 -10.750 -0.9390 0.04052 0.03699 -0.0288 1.0000 0.0114 -10.500 -0.8805 0.04648 0.04343 -0.0311 1.0000 0.0129 -10.250 -0.8997 0.04245 0.03912 -0.0274 1.0000 0.0130 -10.000 -0.9352 0.03404 0.02991 -0.0217 1.0000 0.0121 -9.750 -0.9319 0.03105 0.02659 -0.0191 1.0000 0.0123 -9.500 -0.9214 0.02907 0.02439 -0.0172 1.0000 0.0126 -9.250 -0.9093 0.02703 0.02210 -0.0153 1.0000 0.0128 -9.000 -0.8944 0.02539 0.02026 -0.0136 1.0000 0.0134 -8.750 -0.8767 0.02430 0.01901 -0.0123 1.0000 0.0143 -8.500 -0.8599 0.02263 0.01712 -0.0107 1.0000 0.0146 -8.250 -0.8418 0.02116 0.01546 -0.0093 1.0000 0.0149 -8.000 -0.8216 0.02046 0.01461 -0.0081 1.0000 0.0154 -7.750 -0.8088 0.01796 0.01189 -0.0058 1.0000 0.0162 -7.500 -0.7896 0.01681 0.01069 -0.0048 0.9915 0.0173 -7.250 -0.7561 0.01592 0.00974 -0.0066 0.9834 0.0184 -7.000 -0.7210 0.01521 0.00896 -0.0086 0.9765 0.0206 -6.750 -0.6863 0.01412 0.00776 -0.0106 0.9701 0.0237 -6.500 -0.6502 0.01345 0.00706 -0.0129 0.9635 0.0275 -6.250 -0.6130 0.01281 0.00633 -0.0154 0.9574 0.0317 -6.000 -0.5786 0.01219 0.00570 -0.0173 0.9494 0.0383 -5.750 -0.5446 0.01168 0.00514 -0.0190 0.9423 0.0450 -5.500 -0.5152 0.01139 0.00481 -0.0196 0.9341 0.0524 -5.250 -0.4871 0.01096 0.00438 -0.0200 0.9272 0.0626 -5.000 -0.4635 0.01061 0.00405 -0.0194 0.9195 0.0755 -4.750 -0.4377 0.01029 0.00375 -0.0192 0.9135 0.0938 -4.500 -0.4161 0.00989 0.00347 -0.0181 0.9071 0.1235 -4.250 -0.3949 0.00941 0.00320 -0.0171 0.9015 0.1785 -4.000 -0.3764 0.00878 0.00294 -0.0157 0.8960 0.2686 -3.750 -0.3603 0.00809 0.00268 -0.0137 0.8902 0.3798 -3.500 -0.3465 0.00732 0.00244 -0.0112 0.8853 0.5131 -3.250 -0.3328 0.00681 0.00241 -0.0082 0.8802 0.6381 -3.000 -0.3102 0.00675 0.00245 -0.0069 0.8759 0.6865 -2.750 -0.2854 0.00677 0.00249 -0.0061 0.8722 0.7151 -2.500 -0.2597 0.00682 0.00252 -0.0055 0.8689 0.7326 -2.250 -0.2346 0.00686 0.00255 -0.0048 0.8648 0.7474 -2.000 -0.2088 0.00692 0.00259 -0.0042 0.8611 0.7604 -1.750 -0.1825 0.00698 0.00261 -0.0038 0.8578 0.7704 -1.500 -0.1561 0.00706 0.00268 -0.0033 0.8547 0.7803 -1.250 -0.1307 0.00713 0.00277 -0.0026 0.8509 0.7910 -1.000 -0.1052 0.00721 0.00286 -0.0019 0.8471 0.8018 -0.750 -0.0789 0.00729 0.00292 -0.0014 0.8437 0.8108 -0.500 -0.0519 0.00735 0.00300 -0.0011 0.8405 0.8180 -0.250 -0.0268 0.00738 0.00304 -0.0004 0.8356 0.8253 0.000 0.0000 0.00738 0.00304 0.0000 0.8308 0.8307 0.250 0.0269 0.00739 0.00304 0.0004 0.8254 0.8356 0.500 0.0519 0.00734 0.00299 0.0011 0.8177 0.8404 0.750 0.0789 0.00729 0.00292 0.0014 0.8107 0.8437 1.000 0.1052 0.00721 0.00286 0.0019 0.8018 0.8471 1.250 0.1309 0.00714 0.00278 0.0026 0.7916 0.8509 1.500 0.1560 0.00705 0.00267 0.0034 0.7794 0.8548 1.750 0.1825 0.00698 0.00260 0.0038 0.7700 0.8579 2.000 0.2087 0.00691 0.00258 0.0043 0.7593 0.8611 2.250 0.2346 0.00686 0.00255 0.0048 0.7469 0.8648 2.500 0.2597 0.00682 0.00252 0.0055 0.7318 0.8689 2.750 0.2855 0.00677 0.00249 0.0061 0.7160 0.8722 3.000 0.3108 0.00675 0.00247 0.0068 0.6915 0.8758 3.250 0.3333 0.00680 0.00242 0.0081 0.6419 0.8802 3.500 0.3475 0.00728 0.00243 0.0110 0.5216 0.8853 3.750 0.3606 0.00807 0.00268 0.0137 0.3819 0.8902 4.000 0.3762 0.00880 0.00295 0.0157 0.2660 0.8961 4.250 0.3951 0.00940 0.00320 0.0171 0.1798 0.9015 4.500 0.4164 0.00988 0.00346 0.0181 0.1251 0.9071 4.750 0.4381 0.01026 0.00373 0.0191 0.0963 0.9135 5.000 0.4636 0.01060 0.00405 0.0194 0.0775 0.9196 5.250 0.4873 0.01094 0.00436 0.0200 0.0644 0.9273 5.500 0.5155 0.01136 0.00478 0.0196 0.0526 0.9341 5.750 0.5449 0.01164 0.00509 0.0190 0.0444 0.9422 6.000 0.5791 0.01211 0.00562 0.0172 0.0378 0.9493 6.250 0.6126 0.01290 0.00642 0.0154 0.0305 0.9575 6.500 0.6509 0.01333 0.00692 0.0129 0.0261 0.9633 6.750 0.6842 0.01463 0.00830 0.0110 0.0217 0.9706 7.000 0.7217 0.01510 0.00884 0.0085 0.0195 0.9764 7.250 0.7564 0.01587 0.00967 0.0065 0.0180 0.9834 7.500 0.7892 0.01692 0.01077 0.0048 0.0165 0.9918 7.750 0.8054 0.01880 0.01279 0.0064 0.0157 1.0000 8.000 0.8218 0.02041 0.01457 0.0081 0.0152 1.0000 8.250 0.8410 0.02147 0.01581 0.0095 0.0149 1.0000 8.500 0.8591 0.02292 0.01745 0.0110 0.0143 1.0000 8.750 0.8752 0.02478 0.01954 0.0126 0.0141 1.0000 9.000 0.8914 0.02625 0.02122 0.0142 0.0135 1.0000 9.250 0.9056 0.02796 0.02315 0.0159 0.0130 1.0000 9.500 0.9166 0.03010 0.02554 0.0179 0.0126 1.0000 9.750 0.9224 0.03291 0.02867 0.0203 0.0125 1.0000 10.000 0.9239 0.03596 0.03205 0.0229 0.0124 1.0000 10.250 0.8879 0.04405 0.04083 0.0283 0.0131 1.0000 10.500 0.8550 0.04954 0.04664 0.0323 0.0138 1.0000 10.750 0.8301 0.05444 0.05177 0.0333 0.0138 1.0000 11.000 0.8042 0.06024 0.05776 0.0319 0.0138 1.0000 11.250 0.7740 0.06795 0.06564 0.0274 0.0142 1.0000 11.500 0.5486 0.08516 0.08307 0.0195 0.0197 1.0000 11.750 0.5760 0.08177 0.07970 0.0209 0.0170 1.0000 12.000 0.5662 0.08758 0.08550 0.0186 0.0167 1.0000 12.250 0.5650 0.09082 0.08873 0.0173 0.0162 1.0000 13.250 0.6564 0.14458 0.14224 -0.0147 0.0205 1.0000 13.500 0.4760 0.12429 0.12215 0.0060 0.0220 1.0000 13.750 0.4746 0.12797 0.12583 0.0042 0.0220 1.0000