XFOIL Version 6.96 Calculated polar for: FX 71-L-150/25 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 -0.9957 0.14370 0.14027 0.0164 1.0000 0.0116 -19.250 -1.0155 0.13464 0.13103 0.0108 1.0000 0.0115 -19.000 -1.0284 0.12743 0.12369 0.0064 1.0000 0.0116 -18.750 -1.0429 0.12006 0.11617 0.0020 1.0000 0.0115 -18.500 -1.0542 0.11354 0.10951 -0.0018 1.0000 0.0115 -18.250 -1.0653 0.10722 0.10306 -0.0054 1.0000 0.0115 -18.000 -1.0749 0.10137 0.09708 -0.0086 1.0000 0.0115 -17.750 -1.0819 0.09610 0.09168 -0.0114 1.0000 0.0115 -17.500 -1.0895 0.09090 0.08637 -0.0141 1.0000 0.0115 -17.250 -1.0947 0.08620 0.08156 -0.0164 1.0000 0.0115 -17.000 -1.0999 0.08166 0.07690 -0.0185 1.0000 0.0115 -16.750 -1.1038 0.07743 0.07257 -0.0204 1.0000 0.0116 -16.500 -1.1064 0.07348 0.06851 -0.0221 1.0000 0.0115 -16.250 -1.1087 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0.6677 3.250 0.3609 0.00928 0.00265 0.0011 0.3334 0.6725 3.500 0.3855 0.00976 0.00291 0.0014 0.2778 0.6776 3.750 0.4092 0.01037 0.00322 0.0019 0.2138 0.6823 4.000 0.4323 0.01099 0.00356 0.0024 0.1497 0.6861 4.250 0.4562 0.01148 0.00388 0.0028 0.1075 0.6900 4.500 0.4809 0.01190 0.00417 0.0032 0.0823 0.6943 4.750 0.5060 0.01227 0.00445 0.0035 0.0605 0.6986 5.000 0.5316 0.01259 0.00471 0.0038 0.0491 0.7024 5.250 0.5562 0.01297 0.00502 0.0042 0.0332 0.7056 5.500 0.5811 0.01329 0.00532 0.0046 0.0272 0.7089 5.750 0.6065 0.01356 0.00561 0.0050 0.0220 0.7127 6.000 0.6309 0.01392 0.00594 0.0054 0.0168 0.7167 6.250 0.6556 0.01425 0.00626 0.0059 0.0156 0.7205 6.500 0.6801 0.01457 0.00659 0.0063 0.0151 0.7237 6.750 0.7041 0.01489 0.00695 0.0068 0.0146 0.7266 7.000 0.7276 0.01525 0.00735 0.0074 0.0142 0.7297 7.250 0.7505 0.01564 0.00777 0.0081 0.0139 0.7330 7.500 0.7733 0.01603 0.00819 0.0087 0.0137 0.7365 7.750 0.7952 0.01647 0.00866 0.0095 0.0135 0.7401 8.000 0.8158 0.01695 0.00918 0.0104 0.0133 0.7432 8.250 0.8361 0.01742 0.00970 0.0114 0.0132 0.7465 8.500 0.8557 0.01790 0.01023 0.0125 0.0131 0.7500 8.750 0.8743 0.01842 0.01079 0.0136 0.0130 0.7538 9.000 0.8918 0.01896 0.01136 0.0149 0.0130 0.7574 9.250 0.9064 0.01952 0.01197 0.0166 0.0129 0.7604 9.500 0.9175 0.02009 0.01261 0.0188 0.0128 0.7638 9.750 0.9279 0.02078 0.01336 0.0210 0.0127 0.7675 10.000 0.9380 0.02157 0.01419 0.0228 0.0127 0.7714 10.250 0.9474 0.02249 0.01517 0.0245 0.0126 0.7750 10.500 0.9577 0.02340 0.01615 0.0258 0.0126 0.7785 10.750 0.9672 0.02443 0.01726 0.0272 0.0125 0.7823 11.000 0.9777 0.02544 0.01833 0.0283 0.0125 0.7863 11.500 0.9965 0.02768 0.02071 0.0306 0.0123 0.7949 11.750 1.0041 0.02897 0.02209 0.0317 0.0122 0.7997 12.000 1.0132 0.03018 0.02338 0.0326 0.0121 0.8047 12.250 1.0204 0.03158 0.02487 0.0335 0.0120 0.8110 12.500 1.0269 0.03303 0.02643 0.0344 0.0120 0.8197 12.750 1.0345 0.03438 0.02792 0.0352 0.0119 0.8338 13.000 1.0479 0.03597 0.02979 0.0344 0.0119 0.8878 13.250 1.0792 0.03837 0.03235 0.0289 0.0118 1.0000 13.500 1.0856 0.04021 0.03426 0.0291 0.0118 1.0000 13.750 1.0909 0.04221 0.03631 0.0292 0.0118 1.0000 14.000 1.0952 0.04435 0.03852 0.0293 0.0117 1.0000 14.250 1.0996 0.04652 0.04077 0.0292 0.0117 1.0000 14.500 1.1031 0.04886 0.04317 0.0290 0.0117 1.0000 14.750 1.1059 0.05132 0.04572 0.0286 0.0117 1.0000 15.000 1.1086 0.05393 0.04841 0.0282 0.0117 1.0000 15.250 1.1108 0.05668 0.05124 0.0275 0.0116 1.0000 15.500 1.1119 0.05962 0.05427 0.0268 0.0117 1.0000 15.750 1.1121 0.06276 0.05750 0.0258 0.0116 1.0000 16.000 1.1118 0.06609 0.06092 0.0247 0.0116 1.0000 16.250 1.1110 0.06956 0.06449 0.0234 0.0116 1.0000 16.500 1.1087 0.07334 0.06837 0.0219 0.0115 1.0000 16.750 1.1064 0.07722 0.07235 0.0202 0.0115 1.0000 17.000 1.1021 0.08152 0.07675 0.0184 0.0115 1.0000 17.250 1.0968 0.08609 0.08145 0.0162 0.0115 1.0000 17.500 1.0911 0.09083 0.08630 0.0139 0.0115 1.0000 17.750 1.0844 0.09591 0.09149 0.0113 0.0115 1.0000 18.000 1.0762 0.10140 0.09711 0.0083 0.0115 1.0000 18.250 1.0669 0.10721 0.10305 0.0051 0.0115 1.0000 18.500 1.0569 0.11328 0.10924 0.0017 0.0115 1.0000 18.750 1.0455 0.11986 0.11596 -0.0021 0.0115 1.0000 19.000 1.0337 0.12661 0.12283 -0.0061 0.0115 1.0000