XFOIL Version 6.96 Calculated polar for: NACA 64-008A 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 ------ -------- --------- --------- -------- -------- -------- -9.750 -0.7348 0.08480 0.08271 0.0050 1.0000 0.0049 -9.500 -0.7476 0.07519 0.07311 -0.0050 1.0000 0.0047 -9.250 -0.7664 0.06802 0.06585 -0.0109 1.0000 0.0045 -9.000 -0.7809 0.06175 0.05943 -0.0130 1.0000 0.0045 -8.750 -0.7895 0.05516 0.05264 -0.0140 1.0000 0.0046 -8.500 -0.7953 0.04789 0.04506 -0.0138 1.0000 0.0048 -8.250 -0.8038 0.03794 0.03454 -0.0120 1.0000 0.0052 -8.000 -0.8101 0.02754 0.02319 -0.0087 1.0000 0.0055 -7.750 -0.7952 0.02397 0.01912 -0.0072 1.0000 0.0058 -7.500 -0.7789 0.02086 0.01556 -0.0059 1.0000 0.0062 -7.250 -0.7563 0.01995 0.01453 -0.0054 1.0000 0.0066 -7.000 -0.7329 0.01919 0.01366 -0.0049 1.0000 0.0070 -6.750 -0.7096 0.01827 0.01260 -0.0044 1.0000 0.0075 -6.500 -0.6863 0.01727 0.01142 -0.0037 1.0000 0.0082 -6.250 -0.6620 0.01667 0.01071 -0.0032 1.0000 0.0092 -6.000 -0.6376 0.01614 0.01008 -0.0027 1.0000 0.0098 -5.750 -0.6156 0.01484 0.00861 -0.0018 1.0000 0.0104 -5.500 -0.5948 0.01350 0.00715 -0.0006 1.0000 0.0114 -5.250 -0.5719 0.01286 0.00646 0.0002 1.0000 0.0122 -5.000 -0.5482 0.01247 0.00604 0.0009 1.0000 0.0135 -4.750 -0.5252 0.01197 0.00547 0.0017 1.0000 0.0146 -4.500 -0.5026 0.01145 0.00487 0.0026 1.0000 0.0154 -4.250 -0.4743 0.01097 0.00433 0.0023 0.9973 0.0162 -4.000 -0.4416 0.01054 0.00383 0.0010 0.9921 0.0169 -3.750 -0.4088 0.01011 0.00334 -0.0003 0.9861 0.0181 -3.500 -0.3770 0.00967 0.00283 -0.0013 0.9784 0.0214 -3.250 -0.3449 0.00938 0.00252 -0.0024 0.9701 0.0262 -3.000 -0.3130 0.00909 0.00225 -0.0034 0.9606 0.0392 -2.750 -0.2820 0.00873 0.00202 -0.0043 0.9497 0.0715 -2.500 -0.2533 0.00826 0.00177 -0.0048 0.9365 0.1411 -2.000 -0.2063 0.00649 0.00127 -0.0041 0.9054 0.4959 -1.750 -0.1824 0.00608 0.00120 -0.0033 0.8901 0.5948 -1.500 -0.1588 0.00579 0.00118 -0.0023 0.8752 0.6778 -1.250 -0.1337 0.00566 0.00116 -0.0016 0.8610 0.7223 -1.000 -0.1075 0.00562 0.00112 -0.0011 0.8475 0.7458 -0.750 -0.0809 0.00559 0.00109 -0.0008 0.8343 0.7613 -0.500 -0.0539 0.00559 0.00106 -0.0005 0.8217 0.7736 -0.250 -0.0269 0.00559 0.00104 -0.0003 0.8095 0.7856 0.000 0.0000 0.00558 0.00104 0.0000 0.7974 0.7974 0.250 0.0269 0.00559 0.00104 0.0003 0.7856 0.8095 0.500 0.0539 0.00559 0.00106 0.0005 0.7736 0.8217 0.750 0.0809 0.00559 0.00109 0.0008 0.7613 0.8343 1.000 0.1075 0.00562 0.00112 0.0011 0.7458 0.8475 1.250 0.1337 0.00566 0.00115 0.0016 0.7222 0.8610 1.500 0.1587 0.00579 0.00118 0.0023 0.6779 0.8752 1.750 0.1824 0.00608 0.00120 0.0033 0.5951 0.8901 2.000 0.2061 0.00651 0.00127 0.0041 0.4895 0.9055 2.250 0.2281 0.00746 0.00149 0.0048 0.2881 0.9215 2.500 0.2532 0.00826 0.00177 0.0048 0.1402 0.9365 2.750 0.2820 0.00874 0.00202 0.0043 0.0711 0.9497 3.000 0.3130 0.00909 0.00225 0.0034 0.0393 0.9606 3.250 0.3450 0.00938 0.00252 0.0024 0.0263 0.9701 3.500 0.3771 0.00968 0.00283 0.0013 0.0214 0.9784 3.750 0.4089 0.01011 0.00335 0.0003 0.0181 0.9861 4.000 0.4417 0.01054 0.00384 -0.0010 0.0169 0.9920 4.250 0.4744 0.01097 0.00433 -0.0023 0.0162 0.9973 4.500 0.5027 0.01145 0.00488 -0.0026 0.0155 1.0000 4.750 0.5254 0.01198 0.00547 -0.0017 0.0146 1.0000 5.000 0.5484 0.01246 0.00603 -0.0009 0.0134 1.0000 5.250 0.5720 0.01286 0.00645 -0.0002 0.0122 1.0000 5.500 0.5948 0.01350 0.00715 0.0006 0.0114 1.0000 5.750 0.6155 0.01487 0.00865 0.0018 0.0103 1.0000 6.000 0.6377 0.01614 0.01007 0.0027 0.0098 1.0000 6.250 0.6621 0.01667 0.01071 0.0032 0.0092 1.0000 6.500 0.6863 0.01727 0.01142 0.0037 0.0082 1.0000 6.750 0.7096 0.01826 0.01259 0.0044 0.0075 1.0000 7.000 0.7328 0.01920 0.01367 0.0050 0.0070 1.0000 7.250 0.7562 0.01994 0.01452 0.0054 0.0066 1.0000 7.500 0.7787 0.02084 0.01554 0.0059 0.0062 1.0000 7.750 0.7950 0.02396 0.01910 0.0073 0.0058 1.0000 8.000 0.8099 0.02752 0.02318 0.0088 0.0055 1.0000 8.250 0.8037 0.03782 0.03442 0.0121 0.0052 1.0000 8.500 0.7951 0.04783 0.04499 0.0139 0.0049 1.0000 8.750 0.7892 0.05513 0.05261 0.0141 0.0046 1.0000 9.000 0.7806 0.06171 0.05940 0.0131 0.0045 1.0000 9.250 0.7664 0.06798 0.06581 0.0110 0.0045 1.0000 9.500 0.7477 0.07516 0.07308 0.0051 0.0047 1.0000 9.750 0.7350 0.08480 0.08271 -0.0050 0.0049 1.0000