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 = 0.200 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -14.250 -0.9680 0.07542 0.07036 -0.0328 1.0000 0.0352 -14.000 -0.9685 0.07167 0.06654 -0.0336 1.0000 0.0350 -13.750 -0.9773 0.06752 0.06227 -0.0345 1.0000 0.0348 -13.500 -0.9899 0.06333 0.05792 -0.0353 1.0000 0.0345 -13.250 -1.0017 0.05944 0.05384 -0.0356 1.0000 0.0343 -13.000 -1.0136 0.05576 0.04995 -0.0355 1.0000 0.0340 -12.750 -1.0228 0.05236 0.04633 -0.0350 1.0000 0.0337 -12.500 -1.0298 0.04924 0.04297 -0.0342 1.0000 0.0335 -12.250 -1.0328 0.04646 0.03996 -0.0331 1.0000 0.0334 -12.000 -1.0330 0.04412 0.03741 -0.0319 1.0000 0.0335 -11.750 -1.0294 0.04189 0.03497 -0.0305 1.0000 0.0335 -11.500 -1.0224 0.03979 0.03266 -0.0292 1.0000 0.0337 -11.250 -1.0100 0.03774 0.03043 -0.0282 1.0000 0.0336 -11.000 -0.9949 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0.6786 -1.500 -0.1639 0.01598 0.00970 -0.0014 0.7458 0.6859 -1.250 -0.1364 0.01611 0.00983 -0.0009 0.7421 0.6901 -1.000 -0.1088 0.01622 0.00995 -0.0008 0.7370 0.6955 -0.750 -0.0817 0.01619 0.00988 -0.0009 0.7314 0.7025 -0.500 -0.0545 0.01617 0.00985 -0.0005 0.7268 0.7067 -0.250 -0.0272 0.01624 0.00991 0.0000 0.7232 0.7111 0.000 0.0000 0.01632 0.01003 0.0000 0.7171 0.7171 0.250 0.0272 0.01624 0.00991 0.0000 0.7111 0.7232 0.500 0.0545 0.01617 0.00985 0.0005 0.7067 0.7268 0.750 0.0817 0.01619 0.00988 0.0009 0.7025 0.7313 1.000 0.1088 0.01622 0.00995 0.0008 0.6955 0.7370 1.250 0.1364 0.01611 0.00983 0.0009 0.6901 0.7421 1.500 0.1639 0.01598 0.00970 0.0014 0.6859 0.7458 1.750 0.1906 0.01597 0.00976 0.0016 0.6786 0.7509 2.000 0.2183 0.01588 0.00966 0.0016 0.6718 0.7572 2.250 0.2458 0.01565 0.00944 0.0022 0.6668 0.7614 2.500 0.2724 0.01557 0.00943 0.0026 0.6589 0.7665 2.750 0.3001 0.01535 0.00920 0.0028 0.6508 0.7729 3.000 0.3277 0.01504 0.00887 0.0035 0.6440 0.7775 3.250 0.3539 0.01485 0.00879 0.0040 0.6334 0.7830 3.500 0.3823 0.01454 0.00840 0.0044 0.6248 0.7892 3.750 0.4084 0.01408 0.00800 0.0053 0.6096 0.7938 4.000 0.4346 0.01370 0.00764 0.0061 0.5927 0.7993 4.250 0.4611 0.01345 0.00735 0.0067 0.5750 0.8056 4.500 0.4869 0.01325 0.00720 0.0074 0.5579 0.8107 4.750 0.5127 0.01312 0.00711 0.0081 0.5386 0.8161 5.000 0.5385 0.01303 0.00699 0.0087 0.5153 0.8222 5.250 0.5632 0.01295 0.00693 0.0094 0.4853 0.8279 5.500 0.5867 0.01299 0.00692 0.0104 0.4485 0.8340 5.750 0.6090 0.01322 0.00698 0.0113 0.4025 0.8406 6.000 0.6277 0.01369 0.00719 0.0126 0.3365 0.8466 6.250 0.6426 0.01449 0.00763 0.0143 0.2605 0.8531 6.500 0.6573 0.01539 0.00819 0.0158 0.1951 0.8604 6.750 0.6712 0.01626 0.00879 0.0174 0.1411 0.8678 7.000 0.6844 0.01720 0.00948 0.0192 0.0967 0.8767 7.250 0.6954 0.01831 0.01038 0.0211 0.0638 0.8861 7.500 0.7075 0.01928 0.01130 0.0231 0.0518 0.8971 7.750 0.7223 0.02015 0.01221 0.0245 0.0462 0.9102 8.000 0.7410 0.02108 0.01320 0.0249 0.0427 0.9283 8.500 0.7965 0.02336 0.01554 0.0216 0.0386 1.0000 8.750 0.8096 0.02430 0.01648 0.0228 0.0376 1.0000 9.000 0.8242 0.02531 0.01746 0.0237 0.0368 1.0000 9.250 0.8402 0.02637 0.01846 0.0246 0.0360 1.0000 9.500 0.8599 0.02756 0.01954 0.0251 0.0354 1.0000 9.750 0.8811 0.02867 0.02070 0.0257 0.0349 1.0000 10.000 0.9042 0.02984 0.02192 0.0261 0.0345 1.0000 10.250 0.9282 0.03115 0.02330 0.0263 0.0342 1.0000 10.500 0.9521 0.03257 0.02481 0.0266 0.0340 1.0000 10.750 0.9748 0.03420 0.02657 0.0268 0.0338 1.0000 11.000 0.9954 0.03593 0.02845 0.0272 0.0338 1.0000 11.250 1.0110 0.03781 0.03050 0.0281 0.0337 1.0000 11.500 1.0224 0.03972 0.03260 0.0292 0.0336 1.0000 11.750 1.0298 0.04186 0.03494 0.0305 0.0335 1.0000 12.000 1.0334 0.04395 0.03723 0.0318 0.0333 1.0000 12.250 1.0334 0.04632 0.03981 0.0330 0.0332 1.0000 12.500 1.0302 0.04934 0.04308 0.0341 0.0336 1.0000 12.750 1.0230 0.05228 0.04625 0.0349 0.0336 1.0000 13.000 1.0135 0.05574 0.04993 0.0354 0.0339 1.0000 13.250 1.0004 0.05959 0.05401 0.0355 0.0342 1.0000 13.500 0.9911 0.06331 0.05789 0.0352 0.0346 1.0000 13.750 0.9783 0.06748 0.06223 0.0344 0.0348 1.0000 14.000 0.9688 0.07170 0.06657 0.0334 0.0350 1.0000 14.250 0.9679 0.07550 0.07044 0.0326 0.0352 1.0000 14.500 0.7914 0.10503 0.10097 0.0124 0.0384 1.0000