XFOIL Version 6.94 Calculated polar for: voyager2 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.026 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- -3.000 -0.1687 0.02964 0.01608 -0.0269 1.0000 1.0000 -2.750 -0.1567 0.02928 0.01531 -0.0251 1.0000 1.0000 -2.500 -0.1435 0.02902 0.01454 -0.0233 1.0000 1.0000 -2.250 -0.1300 0.02881 0.01400 -0.0214 1.0000 1.0000 -2.000 -0.1164 0.02865 0.01354 -0.0195 1.0000 1.0000 -1.750 -0.1028 0.02851 0.01314 -0.0175 1.0000 1.0000 -1.500 -0.0892 0.02840 0.01281 -0.0155 1.0000 1.0000 -1.250 -0.0757 0.02831 0.01253 -0.0135 1.0000 1.0000 -1.000 -0.0622 0.02823 0.01230 -0.0114 1.0000 1.0000 -0.750 -0.0489 0.02818 0.01212 -0.0093 1.0000 1.0000 -0.500 -0.0356 0.02814 0.01199 -0.0071 1.0000 1.0000 -0.250 -0.0224 0.02811 0.01190 -0.0050 1.0000 1.0000 0.000 -0.0092 0.02810 0.01179 -0.0028 1.0000 1.0000 0.250 0.0040 0.02810 0.01177 -0.0007 1.0000 1.0000 0.500 0.0173 0.02811 0.01180 0.0015 1.0000 1.0000 0.750 0.0305 0.02814 0.01187 0.0036 1.0000 1.0000 1.000 0.0438 0.02818 0.01199 0.0057 1.0000 1.0000 1.250 0.0572 0.02824 0.01216 0.0078 1.0000 1.0000 1.500 0.0707 0.02832 0.01238 0.0099 1.0000 1.0000 1.750 0.0843 0.02842 0.01274 0.0120 1.0000 1.0000 2.000 0.0979 0.02854 0.01308 0.0141 1.0000 1.0000 2.250 0.1116 0.02869 0.01349 0.0161 1.0000 1.0000 2.500 0.1253 0.02888 0.01397 0.0181 1.0000 1.0000 2.750 0.1388 0.02912 0.01452 0.0200 1.0000 1.0000 3.000 0.1517 0.02941 0.01517 0.0220 1.0000 1.0000 3.250 0.1635 0.02981 0.01595 0.0239 1.0000 1.0000 3.500 0.4232 0.02913 0.01436 -0.0086 0.3184 1.0000 3.750 0.4323 0.03071 0.01488 -0.0055 0.1401 1.0000 4.000 0.4490 0.03212 0.01600 -0.0035 0.1231 1.0000 4.250 0.4669 0.03320 0.01717 -0.0015 0.1165 1.0000 4.500 0.4847 0.03426 0.01837 0.0005 0.1145 1.0000 4.750 0.5030 0.03536 0.01964 0.0027 0.1141 1.0000 5.000 0.5230 0.03651 0.02099 0.0046 0.1146 1.0000