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 = 0.050 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -13.750 -0.7298 0.10912 0.10119 -0.0115 1.0000 0.0510 -13.500 -0.7733 0.09618 0.08802 -0.0196 1.0000 0.0501 -13.250 -0.8083 0.08672 0.07829 -0.0252 1.0000 0.0498 -13.000 -0.8321 0.07984 0.07116 -0.0287 1.0000 0.0496 -12.750 -0.8478 0.07447 0.06556 -0.0308 1.0000 0.0496 -12.500 -0.8578 0.06996 0.06082 -0.0321 1.0000 0.0499 -12.250 -0.8632 0.06605 0.05669 -0.0329 1.0000 0.0504 -12.000 -0.8646 0.06254 0.05295 -0.0333 1.0000 0.0511 -11.750 -0.8619 0.05938 0.04953 -0.0333 1.0000 0.0519 -11.500 -0.8565 0.05641 0.04624 -0.0331 1.0000 0.0532 -11.250 -0.8433 0.05439 0.04420 -0.0328 1.0000 0.0549 -11.000 -0.8311 0.05240 0.04213 -0.0324 1.0000 0.0572 -10.750 -0.8165 0.05036 0.03987 -0.0318 1.0000 0.0603 -10.500 -0.8014 0.04875 0.03830 -0.0313 1.0000 0.0635 -10.250 -0.7834 0.04714 0.03655 -0.0305 1.0000 0.0677 -10.000 -0.7688 0.04557 0.03499 -0.0297 1.0000 0.0720 -9.750 -0.7549 0.04394 0.03334 -0.0289 1.0000 0.0777 -9.500 -0.7440 0.04226 0.03163 -0.0282 1.0000 0.0855 -9.250 -0.7370 0.04044 0.02991 -0.0276 1.0000 0.0957 -9.000 -0.7301 0.03869 0.02826 -0.0270 1.0000 0.1072 -8.750 -0.7237 0.03693 0.02661 -0.0261 1.0000 0.1212 -8.500 -0.7179 0.03520 0.02503 -0.0250 1.0000 0.1363 -8.250 -0.7137 0.03350 0.02350 -0.0236 1.0000 0.1538 -8.000 -0.7110 0.03190 0.02207 -0.0217 1.0000 0.1746 -7.750 -0.7101 0.03035 0.02080 -0.0195 1.0000 0.1993 -7.500 -0.7086 0.02887 0.01961 -0.0174 1.0000 0.2339 -7.250 -0.7077 0.02756 0.01870 -0.0149 1.0000 0.2760 -7.000 -0.7063 0.02664 0.01818 -0.0119 1.0000 0.3224 -6.750 -0.7066 0.02624 0.01810 -0.0080 1.0000 0.3642 -6.500 -0.6874 0.02621 0.01828 -0.0069 0.9821 0.4156 -6.000 -0.6188 0.02710 0.01900 -0.0087 0.9517 0.5003 -5.750 -0.5827 0.02793 0.01967 -0.0090 0.9398 0.5263 -5.500 -0.5465 0.02867 0.02023 -0.0095 0.9298 0.5484 -5.250 -0.5124 0.02927 0.02066 -0.0097 0.9202 0.5669 -5.000 -0.4809 0.02963 0.02081 -0.0099 0.9111 0.5837 -4.750 -0.4531 0.02974 0.02073 -0.0099 0.9016 0.5999 -4.500 -0.4168 0.03025 0.02110 -0.0102 0.8940 0.6100 -4.250 -0.3904 0.03025 0.02094 -0.0099 0.8847 0.6221 -4.000 -0.3683 0.03007 0.02058 -0.0093 0.8756 0.6352 -3.750 -0.3395 0.03019 0.02058 -0.0090 0.8675 0.6444 -3.500 -0.3160 0.03003 0.02029 -0.0085 0.8597 0.6546 -3.250 -0.2972 0.02973 0.01986 -0.0076 0.8513 0.6659 -3.000 -0.2673 0.02980 0.01983 -0.0074 0.8449 0.6732 -2.750 -0.2469 0.02961 0.01955 -0.0065 0.8371 0.6829 -2.500 -0.2237 0.02942 0.01924 -0.0060 0.8309 0.6920 -2.250 -0.2014 0.02933 0.01909 -0.0053 0.8236 0.6992 -2.000 -0.1817 0.02903 0.01869 -0.0046 0.8178 0.7082 -1.750 -0.1592 0.02896 0.01858 -0.0040 0.8108 0.7152 -1.500 -0.1370 0.02879 0.01835 -0.0033 0.8045 0.7232 -1.250 -0.1175 0.02865 0.01815 -0.0024 0.7973 0.7318 -1.000 -0.0910 0.02860 0.01807 -0.0020 0.7907 0.7378 -0.750 -0.0713 0.02844 0.01787 -0.0012 0.7836 0.7460 -0.500 -0.0444 0.02843 0.01786 -0.0010 0.7769 0.7512 -0.250 -0.0238 0.02836 0.01775 -0.0003 0.7703 0.7585 0.000 0.0000 0.02837 0.01777 0.0000 0.7638 0.7638 0.250 0.0238 0.02836 0.01774 0.0003 0.7585 0.7703 0.500 0.0444 0.02843 0.01785 0.0010 0.7512 0.7769 0.750 0.0713 0.02844 0.01787 0.0012 0.7460 0.7836 1.000 0.0910 0.02859 0.01807 0.0020 0.7378 0.7907 1.250 0.1175 0.02865 0.01815 0.0024 0.7318 0.7973 1.500 0.1370 0.02879 0.01835 0.0033 0.7232 0.8045 1.750 0.1592 0.02896 0.01858 0.0040 0.7152 0.8108 2.000 0.1817 0.02903 0.01869 0.0046 0.7082 0.8178 2.250 0.2014 0.02932 0.01909 0.0053 0.6992 0.8236 2.500 0.2237 0.02942 0.01923 0.0060 0.6920 0.8309 2.750 0.2469 0.02962 0.01955 0.0065 0.6829 0.8371 3.000 0.2673 0.02980 0.01982 0.0074 0.6732 0.8449 3.250 0.2973 0.02972 0.01985 0.0076 0.6659 0.8513 3.500 0.3161 0.03003 0.02029 0.0085 0.6546 0.8596 3.750 0.3396 0.03018 0.02057 0.0090 0.6444 0.8675 4.000 0.3684 0.03006 0.02057 0.0093 0.6352 0.8756 4.250 0.3905 0.03024 0.02093 0.0099 0.6221 0.8847 4.500 0.4169 0.03024 0.02109 0.0102 0.6100 0.8940 4.750 0.4532 0.02973 0.02072 0.0099 0.5999 0.9016 5.000 0.4810 0.02962 0.02080 0.0099 0.5837 0.9112 5.250 0.5126 0.02926 0.02065 0.0097 0.5669 0.9203 5.500 0.5466 0.02866 0.02022 0.0095 0.5484 0.9299 5.750 0.5828 0.02792 0.01966 0.0090 0.5262 0.9399 6.000 0.6189 0.02710 0.01900 0.0086 0.5004 0.9518 6.500 0.6876 0.02621 0.01827 0.0069 0.4155 0.9822 6.750 0.7065 0.02623 0.01810 0.0080 0.3643 1.0000 7.000 0.7063 0.02664 0.01817 0.0119 0.3223 1.0000 7.250 0.7078 0.02756 0.01869 0.0149 0.2758 1.0000 7.500 0.7087 0.02887 0.01960 0.0174 0.2338 1.0000 7.750 0.7103 0.03035 0.02080 0.0195 0.1992 1.0000 8.000 0.7113 0.03190 0.02206 0.0216 0.1746 1.0000 8.250 0.7140 0.03350 0.02350 0.0235 0.1536 1.0000 8.500 0.7183 0.03520 0.02503 0.0249 0.1362 1.0000 8.750 0.7237 0.03695 0.02662 0.0261 0.1207 1.0000 9.000 0.7303 0.03870 0.02826 0.0269 0.1070 1.0000 9.250 0.7374 0.04044 0.02990 0.0275 0.0956 1.0000 9.500 0.7447 0.04224 0.03161 0.0281 0.0855 1.0000 9.750 0.7555 0.04393 0.03333 0.0288 0.0777 1.0000 10.000 0.7696 0.04554 0.03495 0.0297 0.0721 1.0000 10.250 0.7841 0.04713 0.03654 0.0304 0.0677 1.0000 10.500 0.8019 0.04876 0.03831 0.0312 0.0633 1.0000 10.750 0.8181 0.05033 0.03985 0.0318 0.0605 1.0000 11.000 0.8321 0.05237 0.04210 0.0323 0.0573 1.0000 11.250 0.8447 0.05438 0.04420 0.0327 0.0550 1.0000 11.500 0.8579 0.05635 0.04618 0.0330 0.0533 1.0000 11.750 0.8629 0.05938 0.04954 0.0332 0.0519 1.0000 12.000 0.8659 0.06250 0.05291 0.0332 0.0511 1.0000 12.250 0.8641 0.06606 0.05670 0.0328 0.0504 1.0000 12.500 0.8587 0.06997 0.06084 0.0320 0.0500 1.0000 12.750 0.8488 0.07448 0.06558 0.0307 0.0497 1.0000 13.000 0.8331 0.07985 0.07118 0.0286 0.0495 1.0000 13.250 0.8093 0.08673 0.07830 0.0251 0.0497 1.0000 13.500 0.7748 0.09611 0.08794 0.0195 0.0502 1.0000 13.750 0.7306 0.10923 0.10129 0.0113 0.0510 1.0000