XFOIL Version 6.94 Calculated polar for: K3311 (smoothed) 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.080 Re = 0.300 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- 0.000 0.4226 0.00790 0.00276 -0.0875 0.7146 0.9853 0.500 0.4849 0.00805 0.00270 -0.0892 0.6936 1.0000 1.000 0.5322 0.00824 0.00271 -0.0875 0.6731 1.0000 1.500 0.5807 0.00846 0.00278 -0.0859 0.6534 1.0000 2.000 0.6298 0.00870 0.00289 -0.0845 0.6341 1.0000 2.500 0.6793 0.00897 0.00303 -0.0831 0.6151 1.0000 3.000 0.7289 0.00925 0.00323 -0.0817 0.5958 1.0000 3.500 0.7782 0.00951 0.00347 -0.0803 0.5753 1.0000 4.000 0.8276 0.00979 0.00375 -0.0790 0.5546 1.0000 4.500 0.8767 0.01012 0.00404 -0.0776 0.5334 1.0000 5.000 0.9253 0.01047 0.00439 -0.0761 0.5107 1.0000 5.500 0.9730 0.01082 0.00477 -0.0744 0.4853 1.0000 6.000 1.0199 0.01124 0.00522 -0.0727 0.4589 1.0000 6.500 1.0647 0.01170 0.00568 -0.0706 0.4266 1.0000 7.000 1.1048 0.01232 0.00620 -0.0677 0.3782 1.0000 7.500 1.1432 0.01313 0.00692 -0.0647 0.3273 1.0000 8.000 1.1763 0.01426 0.00784 -0.0610 0.2668 1.0000 8.500 1.2034 0.01574 0.00903 -0.0565 0.1990 1.0000 9.000 1.2181 0.01778 0.01066 -0.0503 0.1189 1.0000 9.500 1.2148 0.02062 0.01303 -0.0416 0.0534 1.0000 10.000 1.2208 0.02321 0.01568 -0.0350 0.0379 1.0000 10.500 1.2182 0.02665 0.01924 -0.0287 0.0307 1.0000 11.000 1.2299 0.02953 0.02233 -0.0249 0.0275 1.0000 11.500 1.2354 0.03321 0.02621 -0.0214 0.0250 1.0000 12.000 1.2328 0.03806 0.03120 -0.0182 0.0230 1.0000 12.500 1.2395 0.04245 0.03581 -0.0158 0.0212 1.0000 13.000 1.2496 0.04667 0.04027 -0.0141 0.0195 1.0000 13.500 1.2578 0.05134 0.04518 -0.0126 0.0184 1.0000 14.000 1.2627 0.05653 0.05060 -0.0117 0.0173 1.0000 14.500 1.2650 0.06253 0.05684 -0.0108 0.0166 1.0000 15.000 1.2490 0.07210 0.06686 -0.0104 0.0158 1.0000 15.500 1.2311 0.08073 0.07588 -0.0131 0.0155 1.0000 16.000 1.2098 0.09093 0.08646 -0.0171 0.0151 1.0000 16.500 1.1838 0.10295 0.09887 -0.0227 0.0149 1.0000 17.000 1.1492 0.11773 0.11401 -0.0305 0.0150 1.0000 17.500 1.1114 0.13468 0.13131 -0.0405 0.0152 1.0000 18.000 1.0641 0.15575 0.15266 -0.0533 0.0157 1.0000 18.500 1.0229 0.18009 0.17726 -0.0683 0.0166 1.0000