XFOIL Version 6.96 Calculated polar for: WORTMANN FX 77-W-343 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 = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -19.750 -1.0997 0.09446 0.08748 -0.0141 0.4731 0.0206 -19.500 -1.0944 0.09180 0.08476 -0.0148 0.4700 0.0207 -19.250 -1.0885 0.08924 0.08213 -0.0154 0.4667 0.0208 -19.000 -1.0812 0.08686 0.07970 -0.0159 0.4652 0.0209 -18.750 -1.0752 0.08431 0.07710 -0.0164 0.4638 0.0210 -18.500 -1.0665 0.08213 0.07488 -0.0169 0.4623 0.0211 -18.250 -1.0579 0.07993 0.07263 -0.0173 0.4607 0.0212 -18.000 -1.0504 0.07762 0.07025 -0.0177 0.4590 0.0213 -17.750 -1.0402 0.07565 0.06824 -0.0180 0.4573 0.0214 -17.500 -1.0298 0.07371 0.06625 -0.0183 0.4555 0.0216 -17.250 -1.0202 0.07165 0.06414 -0.0186 0.4535 0.0218 -17.000 -1.0098 0.06971 0.06216 -0.0188 0.4513 0.0220 -16.750 -0.9982 0.06791 0.06032 -0.0191 0.4490 0.0223 -16.500 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