XFOIL Version 6.96 Calculated polar for: FX 79-L-120 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 ------ -------- --------- --------- -------- -------- -------- -15.750 -0.9155 0.11002 0.10587 0.0016 1.0000 0.0204 -15.500 -0.9599 0.09558 0.09120 -0.0076 1.0000 0.0203 -15.250 -0.9868 0.08612 0.08155 -0.0136 1.0000 0.0201 -15.000 -1.0126 0.07768 0.07289 -0.0188 1.0000 0.0202 -14.750 -1.0324 0.07091 0.06590 -0.0227 1.0000 0.0202 -14.500 -1.0497 0.06493 0.05968 -0.0258 1.0000 0.0204 -14.250 -1.0633 0.05978 0.05428 -0.0281 1.0000 0.0205 -14.000 -1.0724 0.05552 0.04984 -0.0298 1.0000 0.0209 -13.750 -1.0752 0.05225 0.04646 -0.0308 1.0000 0.0211 -13.500 -1.0778 0.04905 0.04312 -0.0315 1.0000 0.0212 -13.250 -1.0745 0.04687 0.04088 -0.0321 1.0000 0.0217 -13.000 -1.0738 0.04434 0.03822 -0.0324 1.0000 0.0222 -12.750 -1.0715 0.04208 0.03584 -0.0324 1.0000 0.0227 -12.500 -1.0683 0.03998 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