XFOIL Version 6.96 Calculated polar for: FX 71-L-150/30 AIRFOIL 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 ------ -------- --------- --------- -------- -------- -------- -17.500 -0.8325 0.14632 0.14204 0.0160 1.0000 0.0183 -17.250 -0.8957 0.12530 0.12070 0.0032 1.0000 0.0179 -17.000 -0.9279 0.11346 0.10861 -0.0043 1.0000 0.0178 -16.750 -0.9517 0.10419 0.09912 -0.0100 1.0000 0.0177 -16.500 -0.9689 0.09675 0.09148 -0.0143 1.0000 0.0176 -16.250 -0.9831 0.09020 0.08473 -0.0180 1.0000 0.0176 -16.000 -0.9945 0.08444 0.07879 -0.0210 1.0000 0.0176 -15.750 -1.0049 0.07908 0.07324 -0.0235 1.0000 0.0176 -15.500 -1.0112 0.07456 0.06855 -0.0255 1.0000 0.0176 -15.250 -1.0158 0.07047 0.06430 -0.0271 1.0000 0.0176 -15.000 -1.0198 0.06661 0.06027 -0.0284 1.0000 0.0178 -14.750 -1.0205 0.06333 0.05685 -0.0293 1.0000 0.0177 -14.500 -1.0202 0.06030 0.05369 -0.0300 1.0000 0.0178 -14.250 -1.0195 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0.00544 0.0039 0.3872 0.7259 5.000 0.5416 0.01358 0.00570 0.0048 0.3192 0.7302 5.500 0.5806 0.01498 0.00654 0.0068 0.1965 0.7381 5.750 0.6015 0.01556 0.00698 0.0076 0.1618 0.7427 6.000 0.6230 0.01609 0.00740 0.0083 0.1337 0.7471 6.250 0.6443 0.01658 0.00783 0.0091 0.1097 0.7508 6.500 0.6643 0.01718 0.00833 0.0100 0.0875 0.7549 6.750 0.6854 0.01770 0.00880 0.0108 0.0714 0.7591 7.000 0.7050 0.01825 0.00931 0.0117 0.0573 0.7630 7.250 0.7245 0.01880 0.00986 0.0127 0.0477 0.7674 7.500 0.7440 0.01937 0.01042 0.0137 0.0392 0.7723 7.750 0.7619 0.01998 0.01105 0.0149 0.0339 0.7767 8.000 0.7790 0.02060 0.01172 0.0162 0.0307 0.7817 8.250 0.7945 0.02129 0.01246 0.0176 0.0284 0.7873 8.500 0.8094 0.02191 0.01320 0.0192 0.0267 0.7932 8.750 0.8215 0.02259 0.01396 0.0211 0.0254 0.8009 9.000 0.8328 0.02328 0.01476 0.0231 0.0244 0.8113 9.250 0.8442 0.02406 0.01567 0.0248 0.0237 0.8253 9.500 0.8564 0.02488 0.01664 0.0261 0.0227 0.8446 9.750 0.8748 0.02583 0.01779 0.0259 0.0219 0.8927 10.000 0.8991 0.02706 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15.000 1.0206 0.06665 0.06032 0.0282 0.0177 1.0000 15.250 1.0183 0.07027 0.06409 0.0270 0.0177 1.0000 15.500 1.0124 0.07456 0.06855 0.0253 0.0176 1.0000 15.750 1.0058 0.07912 0.07328 0.0233 0.0176 1.0000 16.000 0.9974 0.08415 0.07849 0.0209 0.0176 1.0000 16.250 0.9849 0.09011 0.08463 0.0178 0.0176 1.0000 16.500 0.9696 0.09689 0.09162 0.0140 0.0176 1.0000 16.750 0.9521 0.10439 0.09932 0.0096 0.0177 1.0000 17.000 0.9324 0.11277 0.10790 0.0045 0.0178 1.0000 17.250 0.8993 0.12478 0.12017 -0.0030 0.0179 1.0000