XFOIL Version 6.96 Calculated polar for: GOE 443 AIRFOIL 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 -0.5486 0.10775 0.10623 0.0153 1.0000 0.0052 -9.750 -0.5477 0.10332 0.10180 0.0137 1.0000 0.0055 -9.250 -0.5472 0.09418 0.09268 0.0105 1.0000 0.0057 -3.000 -0.3442 0.01314 0.00804 0.0022 0.9983 0.0108 -2.750 -0.3158 0.00908 0.00367 0.0032 0.9955 0.0046 -2.500 -0.2859 0.00794 0.00235 0.0030 0.9915 0.0035 -2.250 -0.2532 0.00741 0.00170 0.0019 0.9876 0.0029 -2.000 -0.2217 0.00710 0.00133 0.0011 0.9818 0.0026 -1.750 -0.1886 0.00689 0.00105 -0.0001 0.9769 0.0024 -1.500 -0.1567 0.00673 0.00085 -0.0010 0.9708 0.0024 -1.250 -0.1244 0.00661 0.00072 -0.0021 0.9630 0.0026 -1.000 -0.0911 0.00651 0.00063 -0.0034 0.9518 0.0033 -0.750 -0.0668 0.00490 0.00047 -0.0036 0.9317 0.4450 -0.500 -0.0416 0.00444 0.00038 -0.0032 0.8877 0.5888 -0.250 -0.0212 0.00412 0.00036 -0.0016 0.8413 0.7198 0.000 0.0000 0.00400 0.00036 0.0000 0.7994 0.7985 0.250 0.0212 0.00412 0.00036 0.0016 0.7212 0.8416 0.500 0.0415 0.00445 0.00038 0.0032 0.5879 0.8863 0.750 0.0667 0.00489 0.00047 0.0036 0.4462 0.9316 1.000 0.0910 0.00651 0.00063 0.0034 0.0033 0.9516 1.250 0.1245 0.00661 0.00072 0.0021 0.0026 0.9629 1.500 0.1569 0.00673 0.00085 0.0009 0.0024 0.9707 1.750 0.1888 0.00689 0.00105 0.0000 0.0024 0.9767 2.000 0.2219 0.00710 0.00132 -0.0012 0.0026 0.9817 2.250 0.2532 0.00741 0.00171 -0.0019 0.0029 0.9875 2.500 0.2863 0.00796 0.00238 -0.0030 0.0035 0.9918 2.750 0.3163 0.00911 0.00370 -0.0033 0.0046 0.9957 3.000 0.3443 0.01315 0.00805 -0.0022 0.0108 0.9982 3.750 0.3978 0.00661 0.00258 0.0030 0.0109 1.0000 4.000 0.4184 0.00792 0.00417 0.0046 0.0108 1.0000 4.250 0.4448 0.00798 0.00439 0.0061 0.0086 1.0000 4.500 0.4644 0.00931 0.00590 0.0072 0.0074 1.0000 4.750 0.4789 0.01174 0.00853 0.0080 0.0066 1.0000 5.000 0.5165 0.03148 0.02842 0.0083 0.0064 1.0000 5.250 0.5351 0.03471 0.03188 0.0099 0.0063 1.0000 5.500 0.5530 0.03811 0.03549 0.0112 0.0063 1.0000 5.750 0.5712 0.04152 0.03910 0.0123 0.0062 1.0000 6.000 0.5926 0.04514 0.04291 0.0133 0.0056 1.0000 6.250 0.6076 0.04933 0.04727 0.0135 0.0053 1.0000 6.500 0.6207 0.05370 0.05178 0.0132 0.0048 1.0000 6.750 0.6313 0.05820 0.05640 0.0124 0.0046 1.0000 7.000 0.6397 0.06285 0.06116 0.0109 0.0047 1.0000 7.250 0.6462 0.06769 0.06607 0.0086 0.0044 1.0000 7.500 0.6503 0.07258 0.07102 0.0055 0.0044 1.0000 7.750 0.6520 0.07765 0.07612 0.0013 0.0043 1.0000 8.000 0.6466 0.08217 0.08063 -0.0028 0.0043 1.0000 8.250 0.6432 0.08638 0.08482 -0.0057 0.0048 1.0000