XFOIL Version 6.96 Calculated polar for: FX 78-K-161 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 ------ -------- --------- --------- -------- -------- -------- -12.750 -0.5483 0.06474 0.06019 -0.0856 0.7468 0.0201 -12.500 -0.5807 0.05844 0.05373 -0.0879 0.7455 0.0198 -12.250 -0.6128 0.05336 0.04840 -0.0876 0.7440 0.0199 -12.000 -0.6436 0.04892 0.04364 -0.0854 0.7426 0.0202 -11.750 -0.6687 0.04522 0.03958 -0.0820 0.7412 0.0205 -11.500 -0.6904 0.04196 0.03589 -0.0779 0.7398 0.0212 -11.250 -0.6896 0.04047 0.03430 -0.0754 0.7386 0.0215 -11.000 -0.6875 0.03912 0.03281 -0.0728 0.7375 0.0218 -10.750 -0.6806 0.03856 0.03221 -0.0704 0.7365 0.0224 -10.500 -0.6791 0.03723 0.03069 -0.0673 0.7352 0.0228 -10.250 -0.6736 0.03670 0.03007 -0.0645 0.7325 0.0239 -10.000 -0.6684 0.03534 0.02842 -0.0617 0.7304 0.0249 -9.750 -0.6616 0.03384 0.02650 -0.0590 0.7286 0.0260 -9.500 -0.6470 0.03274 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