XFOIL Version 6.94 Calculated polar for: Agora0 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.008 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- -3.000 -0.0337 0.05513 0.04021 -0.0067 0.9992 1.0008 -2.750 -0.0542 0.05325 0.03842 -0.0043 0.9992 1.0008 -2.500 -0.0733 0.05128 0.03636 -0.0028 0.9992 1.0008 -2.250 -0.0634 0.05002 0.03438 -0.0070 0.9992 1.0008 -2.000 -0.0331 0.05002 0.03331 -0.0119 0.9992 1.0008 -1.750 -0.0053 0.05047 0.03292 -0.0141 0.9992 1.0008 -1.500 0.0196 0.05106 0.03290 -0.0151 0.9992 1.0008 -1.250 0.0429 0.05173 0.03311 -0.0156 0.9992 1.0008 -1.000 0.0653 0.05246 0.03351 -0.0158 0.9992 1.0008 -0.750 0.0869 0.05328 0.03409 -0.0159 0.9992 1.0008 -0.500 0.1079 0.05419 0.03485 -0.0161 0.9992 1.0008 -0.250 0.1282 0.05522 0.03583 -0.0163 0.9992 1.0008 0.000 0.1474 0.05645 0.03708 -0.0167 0.9992 1.0008 0.250 0.1649 0.05798 0.03873 -0.0175 0.9992 1.0008 0.500 0.1786 0.06011 0.04105 -0.0188 0.9992 1.0008 0.750 0.1851 0.06333 0.04444 -0.0213 0.9992 1.0008 1.000 0.1861 0.06737 0.04849 -0.0245 0.9992 1.0008 1.250 0.1887 0.07125 0.05230 -0.0274 0.9992 1.0008 1.500 0.1939 0.07485 0.05580 -0.0300 0.9992 1.0008 1.750 0.2009 0.07828 0.05912 -0.0324 0.9992 1.0008 2.000 0.2092 0.08161 0.06233 -0.0345 0.9992 1.0008 2.250 0.2183 0.08486 0.06546 -0.0366 0.9992 1.0008 2.500 0.2279 0.08806 0.06854 -0.0385 0.9992 1.0008 2.750 0.2380 0.09122 0.07159 -0.0403 0.9992 1.0008 3.000 0.2484 0.09437 0.07463 -0.0421 0.9992 1.0008 3.250 0.2592 0.09752 0.07766 -0.0438 0.9992 1.0008 3.500 0.2701 0.10067 0.08069 -0.0454 0.9992 1.0008 3.750 0.2813 0.10381 0.08372 -0.0471 0.9992 1.0008 4.000 0.2927 0.10695 0.08675 -0.0487 0.9992 1.0008 4.250 0.3042 0.11009 0.08978 -0.0503 0.9992 1.0008 4.500 0.3158 0.11324 0.09282 -0.0519 0.9992 1.0008 4.750 0.3275 0.11639 0.09587 -0.0535 0.9992 1.0008 5.000 0.3394 0.11955 0.09893 -0.0551 0.9992 1.0008