XFOIL Version 6.96 Calculated polar for: NACA 16-006 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -9.000 -0.5166 0.08591 0.08258 -0.0164 1.0000 0.0171 -8.750 -0.5210 0.08124 0.07793 -0.0186 1.0000 0.0172 -5.500 -0.5810 0.03940 0.03437 -0.0067 1.0000 0.0081 -5.250 -0.5705 0.03576 0.03042 -0.0041 1.0000 0.0077 -5.000 -0.5573 0.03237 0.02664 -0.0014 1.0000 0.0074 -4.750 -0.5420 0.02912 0.02301 0.0012 1.0000 0.0071 -4.500 -0.5242 0.02616 0.01963 0.0037 1.0000 0.0071 -4.250 -0.5031 0.02422 0.01732 0.0058 1.0000 0.0083 -4.000 -0.4819 0.02198 0.01463 0.0078 1.0000 0.0091 -3.750 -0.4593 0.01945 0.01169 0.0094 1.0000 0.0092 -3.500 -0.4357 0.01718 0.00911 0.0108 1.0000 0.0096 -3.250 -0.4130 0.01550 0.00725 0.0121 1.0000 0.0103 -3.000 -0.3909 0.01452 0.00616 0.0133 1.0000 0.0126 -2.750 -0.3687 0.01367 0.00518 0.0145 1.0000 0.0158 -2.500 -0.3463 0.01285 0.00425 0.0157 1.0000 0.0211 -2.250 -0.3233 0.01221 0.00357 0.0166 1.0000 0.0411 -2.000 -0.3022 0.01092 0.00309 0.0172 1.0000 0.2285 -1.750 -0.2892 0.00864 0.00282 0.0199 1.0000 0.7247 -1.500 -0.2420 0.00881 0.00340 0.0177 1.0000 0.9394 -1.250 -0.1173 0.00940 0.00364 -0.0022 1.0000 0.9909 -1.000 -0.0797 0.00935 0.00349 -0.0048 1.0000 0.9957 -0.750 -0.0433 0.00929 0.00336 -0.0071 1.0000 0.9995 -0.500 -0.0263 0.00925 0.00328 -0.0053 1.0000 1.0000 -0.250 -0.0130 0.00922 0.00324 -0.0027 1.0000 1.0000 0.000 0.0000 0.00921 0.00322 0.0000 1.0000 1.0000 0.250 0.0130 0.00922 0.00324 0.0027 1.0000 1.0000 0.500 0.0263 0.00925 0.00328 0.0053 1.0000 1.0000 0.750 0.0433 0.00929 0.00336 0.0071 0.9995 1.0000 1.000 0.0797 0.00936 0.00349 0.0048 0.9957 1.0000 1.250 0.1174 0.00940 0.00364 0.0022 0.9909 1.0000 1.500 0.2421 0.00881 0.00340 -0.0177 0.9391 1.0000 1.750 0.2892 0.00865 0.00282 -0.0198 0.7227 1.0000 2.000 0.3022 0.01093 0.00310 -0.0173 0.2277 1.0000 2.250 0.3234 0.01221 0.00357 -0.0166 0.0410 1.0000 2.500 0.3464 0.01286 0.00426 -0.0157 0.0211 1.0000 2.750 0.3688 0.01367 0.00518 -0.0146 0.0158 1.0000 3.000 0.3910 0.01453 0.00616 -0.0133 0.0126 1.0000 3.250 0.4131 0.01550 0.00726 -0.0121 0.0103 1.0000 3.500 0.4358 0.01718 0.00911 -0.0108 0.0096 1.0000 3.750 0.4595 0.01946 0.01171 -0.0094 0.0092 1.0000 4.000 0.4821 0.02200 0.01467 -0.0078 0.0091 1.0000 4.250 0.5034 0.02418 0.01728 -0.0058 0.0083 1.0000 4.500 0.5244 0.02617 0.01964 -0.0038 0.0071 1.0000 4.750 0.5421 0.02912 0.02301 -0.0013 0.0071 1.0000 5.000 0.5575 0.03238 0.02665 0.0014 0.0074 1.0000 5.250 0.5706 0.03577 0.03043 0.0041 0.0077 1.0000 5.500 0.5811 0.03940 0.03437 0.0067 0.0081 1.0000 7.500 0.6282 0.07266 0.06897 0.0191 0.0171 1.0000 9.500 0.6300 0.10746 0.10389 -0.0004 0.0166 1.0000 10.500 0.5050 0.11112 0.10769 0.0080 0.0170 1.0000 11.000 0.5039 0.11871 0.11526 0.0055 0.0169 1.0000