XFOIL Version 6.96 Calculated polar for: FX 73-CL2-152 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 ------ -------- --------- --------- -------- -------- -------- -14.500 -0.5191 0.08444 0.08189 -0.0910 0.9873 0.0211 -14.250 -0.5351 0.07692 0.07429 -0.0975 0.9865 0.0213 -14.000 -0.5462 0.06999 0.06728 -0.1043 0.9857 0.0215 -13.750 -0.5694 0.06409 0.06131 -0.1072 0.9818 0.0216 -13.500 -0.5873 0.05743 0.05457 -0.1133 0.9790 0.0218 -13.250 -0.6039 0.04995 0.04697 -0.1220 0.9763 0.0219 -13.000 -0.6367 0.04403 0.04095 -0.1253 0.9688 0.0219 -12.750 -0.6562 0.03644 0.03324 -0.1338 0.9615 0.0220 -12.500 -0.6496 0.02923 0.02586 -0.1454 0.9549 0.0221 -12.250 -0.6242 0.02359 0.02004 -0.1570 0.9484 0.0223 -12.000 -0.5897 0.02081 0.01710 -0.1641 0.9420 0.0227 -11.750 -0.5590 0.01944 0.01564 -0.1671 0.9368 0.0229 -11.500 -0.5287 0.01835 0.01447 -0.1694 0.9300 0.0232 -11.250 -0.4902 0.01732 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