XFOIL Version 6.96 Calculated polar for: FX 83-W-108 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 ------ -------- --------- --------- -------- -------- -------- -11.750 -0.3764 0.12086 0.11912 -0.0412 1.0000 0.0180 -11.500 -0.3831 0.11491 0.11319 -0.0436 1.0000 0.0194 -11.250 -0.6678 0.03329 0.03080 -0.1123 0.9845 0.0143 -11.000 -0.6483 0.02812 0.02522 -0.1205 0.9797 0.0144 -10.750 -0.6279 0.02578 0.02266 -0.1229 0.9728 0.0147 -10.500 -0.6024 0.02310 0.01969 -0.1261 0.9688 0.0148 -10.250 -0.5779 0.02159 0.01798 -0.1273 0.9613 0.0151 -10.000 -0.5462 0.01997 0.01616 -0.1300 0.9574 0.0152 -9.750 -0.5125 0.01873 0.01474 -0.1326 0.9531 0.0154 -9.500 -0.4805 0.01694 0.01273 -0.1352 0.9467 0.0156 -9.250 -0.4472 0.01496 0.01052 -0.1381 0.9407 0.0162 -9.000 -0.4149 0.01419 0.00965 -0.1398 0.9322 0.0166 -8.750 -0.3816 0.01367 0.00905 -0.1414 0.9243 0.0171 -8.500 -0.3517 0.01322 0.00852 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1.0000 11.750 1.4844 0.02463 0.01851 -0.0738 0.0192 1.0000 12.000 1.4942 0.02584 0.01977 -0.0720 0.0184 1.0000 12.250 1.4989 0.02747 0.02148 -0.0697 0.0177 1.0000 12.500 1.5105 0.02858 0.02267 -0.0683 0.0175 1.0000 12.750 1.5302 0.02905 0.02316 -0.0677 0.0169 1.0000 13.000 1.5371 0.03058 0.02478 -0.0659 0.0167 1.0000 13.250 1.5513 0.03151 0.02575 -0.0649 0.0162 1.0000 13.500 1.5617 0.03275 0.02705 -0.0636 0.0158 1.0000 13.750 1.5698 0.03421 0.02858 -0.0622 0.0155 1.0000 14.000 1.5802 0.03550 0.02991 -0.0610 0.0151 1.0000 14.250 1.5867 0.03715 0.03163 -0.0596 0.0148 1.0000 14.500 1.5900 0.03910 0.03364 -0.0581 0.0144 1.0000 14.750 1.5881 0.04161 0.03625 -0.0564 0.0140 1.0000 15.000 1.5862 0.04419 0.03895 -0.0549 0.0137 1.0000 15.250 1.5916 0.04612 0.04096 -0.0539 0.0137 1.0000 15.500 1.5998 0.04779 0.04271 -0.0531 0.0135 1.0000 15.750 1.6046 0.04987 0.04488 -0.0523 0.0133 1.0000 16.000 1.6088 0.05206 0.04717 -0.0516 0.0130 1.0000 16.250 1.6103 0.05461 0.04981 -0.0509 0.0128 1.0000 16.500 1.6145 0.05688 0.05216 -0.0504 0.0126 1.0000 16.750 1.6155 0.05958 0.05494 -0.0500 0.0124 1.0000 17.000 1.6185 0.06211 0.05756 -0.0497 0.0121 1.0000 17.250 1.6177 0.06516 0.06070 -0.0496 0.0119 1.0000 17.500 1.6166 0.06833 0.06396 -0.0496 0.0117 1.0000 17.750 1.6149 0.07165 0.06735 -0.0497 0.0115 1.0000 18.000 1.6108 0.07533 0.07111 -0.0501 0.0112 1.0000 18.250 1.6009 0.07991 0.07580 -0.0506 0.0111 1.0000 18.500 1.5875 0.08510 0.08111 -0.0516 0.0108 1.0000 18.750 1.5707 0.09092 0.08707 -0.0528 0.0107 1.0000