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 = 0.500 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -19.500 -0.9878 0.14404 0.14065 0.0156 1.0000 0.0117 -19.250 -1.0053 0.13557 0.13202 0.0104 1.0000 0.0116 -19.000 -1.0213 0.12774 0.12404 0.0057 1.0000 0.0116 -18.750 -1.0350 0.12060 0.11676 0.0015 1.0000 0.0115 -18.500 -1.0465 0.11407 0.11009 -0.0022 1.0000 0.0115 -18.250 -1.0577 0.10779 0.10368 -0.0057 1.0000 0.0115 -18.000 -1.0668 0.10208 0.09784 -0.0088 1.0000 0.0115 -17.750 -1.0755 0.09654 0.09218 -0.0117 1.0000 0.0115 -17.500 -1.0834 0.09130 0.08681 -0.0144 1.0000 0.0115 -17.250 -1.0888 0.08661 0.08201 -0.0167 1.0000 0.0114 -17.000 -1.0941 0.08205 0.07733 -0.0188 1.0000 0.0115 -16.750 -1.0988 0.07767 0.07285 -0.0207 1.0000 0.0115 -16.500 -1.1020 0.07367 0.06875 -0.0224 1.0000 0.0115 -16.250 -1.1043 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0.4549 0.6510 3.000 0.3378 0.00886 0.00240 0.0005 0.4076 0.6542 3.250 0.3631 0.00924 0.00258 0.0009 0.3535 0.6576 3.500 0.3880 0.00969 0.00281 0.0012 0.2995 0.6612 3.750 0.4130 0.01014 0.00305 0.0015 0.2510 0.6647 4.000 0.4369 0.01065 0.00335 0.0020 0.1977 0.6675 4.250 0.4610 0.01114 0.00365 0.0024 0.1544 0.6703 4.500 0.4853 0.01159 0.00395 0.0028 0.1195 0.6735 4.750 0.5099 0.01201 0.00425 0.0032 0.0914 0.6770 5.000 0.5354 0.01233 0.00451 0.0035 0.0764 0.6805 5.250 0.5601 0.01269 0.00481 0.0040 0.0593 0.6836 5.500 0.5847 0.01306 0.00512 0.0044 0.0456 0.6868 6.000 0.6337 0.01381 0.00577 0.0053 0.0275 0.6935 6.250 0.6581 0.01414 0.00610 0.0058 0.0213 0.6967 6.500 0.6821 0.01450 0.00645 0.0063 0.0173 0.7006 6.750 0.7060 0.01487 0.00680 0.0068 0.0159 0.7046 7.000 0.7298 0.01522 0.00715 0.0073 0.0153 0.7079 7.250 0.7533 0.01554 0.00752 0.0079 0.0150 0.7106 7.500 0.7763 0.01590 0.00791 0.0086 0.0146 0.7133 7.750 0.7988 0.01629 0.00833 0.0093 0.0143 0.7162 8.000 0.8207 0.01670 0.00876 0.0101 0.0141 0.7189 8.250 0.8414 0.01713 0.00924 0.0110 0.0138 0.7213 8.500 0.8614 0.01757 0.00973 0.0120 0.0136 0.7237 8.750 0.8804 0.01805 0.01026 0.0132 0.0134 0.7263 9.000 0.8978 0.01859 0.01084 0.0145 0.0132 0.7291 9.250 0.9144 0.01913 0.01143 0.0159 0.0131 0.7319 9.500 0.9258 0.01973 0.01208 0.0181 0.0130 0.7345 9.750 0.9351 0.02037 0.01279 0.0206 0.0129 0.7374 10.000 0.9453 0.02106 0.01355 0.0227 0.0128 0.7405 10.250 0.9547 0.02186 0.01443 0.0246 0.0127 0.7438 10.500 0.9642 0.02275 0.01539 0.0262 0.0126 0.7475 10.750 0.9741 0.02368 0.01640 0.0276 0.0126 0.7519 11.000 0.9829 0.02476 0.01757 0.0289 0.0125 0.7569 11.250 0.9918 0.02590 0.01878 0.0301 0.0125 0.7623 11.500 1.0007 0.02705 0.02002 0.0312 0.0124 0.7691 11.750 1.0081 0.02834 0.02141 0.0323 0.0122 0.7765 12.000 1.0163 0.02955 0.02272 0.0333 0.0123 0.7858 12.250 1.0215 0.03092 0.02426 0.0345 0.0121 0.8010 12.500 1.0322 0.03215 0.02583 0.0348 0.0121 0.8870 12.750 1.0701 0.03436 0.02822 0.0284 0.0119 1.0000 13.000 1.0764 0.03611 0.03004 0.0288 0.0119 1.0000 13.250 1.0821 0.03796 0.03196 0.0291 0.0118 1.0000 13.500 1.0883 0.03982 0.03387 0.0293 0.0118 1.0000 13.750 1.0923 0.04191 0.03604 0.0295 0.0118 1.0000 14.000 1.0964 0.04405 0.03825 0.0295 0.0118 1.0000 14.250 1.1005 0.04624 0.04051 0.0294 0.0117 1.0000 14.500 1.1031 0.04862 0.04297 0.0292 0.0117 1.0000 14.750 1.1049 0.05121 0.04563 0.0289 0.0116 1.0000 15.000 1.1068 0.05387 0.04838 0.0284 0.0116 1.0000 15.250 1.1088 0.05662 0.05120 0.0278 0.0116 1.0000 15.500 1.1086 0.05974 0.05442 0.0270 0.0115 1.0000 15.750 1.1087 0.06291 0.05768 0.0260 0.0115 1.0000 16.000 1.1087 0.06617 0.06103 0.0250 0.0116 1.0000 16.250 1.1065 0.06983 0.06479 0.0236 0.0115 1.0000 16.500 1.1038 0.07366 0.06873 0.0221 0.0114 1.0000 16.750 1.1006 0.07766 0.07283 0.0205 0.0115 1.0000 17.000 1.0973 0.08181 0.07709 0.0186 0.0115 1.0000 17.250 1.0913 0.08648 0.08188 0.0165 0.0115 1.0000 17.500 1.0841 0.09145 0.08697 0.0141 0.0114 1.0000 17.750 1.0776 0.09648 0.09211 0.0115 0.0115 1.0000 18.000 1.0685 0.10208 0.09784 0.0086 0.0114 1.0000 18.250 1.0599 0.10773 0.10362 0.0055 0.0115 1.0000 18.500 1.0495 0.11384 0.10986 0.0021 0.0115 1.0000 18.750 1.0366 0.12063 0.11679 -0.0018 0.0115 1.0000 19.000 1.0240 0.12758 0.12387 -0.0058 0.0116 1.0000