XFOIL Version 6.96 Calculated polar for: NACA 64-206 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -8.250 -0.5409 0.08484 0.08325 -0.0098 1.0000 0.0049 -8.000 -0.5408 0.08082 0.07925 -0.0121 1.0000 0.0049 -7.750 -0.5443 0.07658 0.07504 -0.0150 1.0000 0.0049 -7.500 -0.5409 0.07126 0.06971 -0.0216 1.0000 0.0049 -7.250 -0.5348 0.06609 0.06451 -0.0261 1.0000 0.0049 -7.000 -0.5270 0.06091 0.05926 -0.0295 1.0000 0.0049 -6.750 -0.5305 0.05132 0.04949 -0.0342 1.0000 0.0052 -6.500 -0.5193 0.04655 0.04458 -0.0357 1.0000 0.0054 -6.250 -0.5049 0.04341 0.04132 -0.0365 1.0000 0.0057 -6.000 -0.4885 0.03999 0.03775 -0.0369 1.0000 0.0059 -5.750 -0.4704 0.03742 0.03503 -0.0370 1.0000 0.0070 -4.000 -0.2983 0.01470 0.01034 -0.0358 0.9958 0.0087 -3.750 -0.2645 0.01137 0.00663 -0.0367 0.9940 0.0081 -3.500 -0.2323 0.01003 0.00514 -0.0375 0.9909 0.0090 -3.250 -0.1996 0.00874 0.00369 -0.0387 0.9876 0.0106 -3.000 -0.1654 0.00793 0.00281 -0.0402 0.9846 0.0124 -2.750 -0.1304 0.00751 0.00236 -0.0419 0.9817 0.0148 -2.500 -0.0994 0.00719 0.00199 -0.0426 0.9745 0.0173 -2.250 -0.0660 0.00689 0.00164 -0.0439 0.9688 0.0186 -2.000 -0.0359 0.00648 0.00114 -0.0443 0.9592 0.0283 -1.750 -0.0072 0.00581 0.00090 -0.0448 0.9486 0.1685 -1.500 0.0187 0.00467 0.00072 -0.0452 0.9366 0.4801 -1.250 0.0449 0.00430 0.00067 -0.0450 0.9240 0.5973 -1.000 0.0707 0.00403 0.00067 -0.0445 0.9113 0.6947 -0.750 0.0966 0.00390 0.00067 -0.0440 0.8988 0.7552 -0.500 0.1221 0.00380 0.00069 -0.0434 0.8860 0.8045 -0.250 0.1478 0.00376 0.00070 -0.0427 0.8731 0.8383 0.000 0.1731 0.00373 0.00072 -0.0420 0.8598 0.8671 0.250 0.1990 0.00374 0.00073 -0.0414 0.8446 0.8846 0.500 0.2246 0.00376 0.00074 -0.0408 0.8269 0.9004 0.750 0.2497 0.00381 0.00075 -0.0400 0.8063 0.9164 1.000 0.2735 0.00388 0.00074 -0.0389 0.7710 0.9328 1.250 0.2967 0.00400 0.00073 -0.0377 0.7256 0.9516 1.500 0.3237 0.00413 0.00073 -0.0375 0.6779 0.9732 1.750 0.3553 0.00440 0.00078 -0.0384 0.6091 1.0000 2.000 0.3815 0.00475 0.00087 -0.0383 0.5355 1.0000 2.250 0.4036 0.00594 0.00114 -0.0379 0.2945 1.0000 2.500 0.4269 0.00711 0.00150 -0.0377 0.0848 1.0000 2.750 0.4533 0.00764 0.00180 -0.0376 0.0264 1.0000 3.000 0.4807 0.00797 0.00217 -0.0375 0.0193 1.0000 3.250 0.5079 0.00832 0.00257 -0.0374 0.0159 1.0000 3.500 0.5345 0.00883 0.00314 -0.0372 0.0135 1.0000 3.750 0.5594 0.00980 0.00425 -0.0367 0.0123 1.0000 4.000 0.5845 0.01070 0.00524 -0.0362 0.0114 1.0000 4.250 0.6114 0.01110 0.00568 -0.0360 0.0102 1.0000 4.500 0.6376 0.01169 0.00632 -0.0358 0.0089 1.0000 4.750 0.6634 0.01250 0.00723 -0.0354 0.0081 1.0000 5.000 0.6891 0.01345 0.00827 -0.0350 0.0075 1.0000 5.250 0.7145 0.01429 0.00917 -0.0348 0.0066 1.0000 5.500 0.7375 0.01734 0.01260 -0.0337 0.0054 1.0000 5.750 0.7606 0.02082 0.01649 -0.0323 0.0051 1.0000 8.750 0.8051 0.08366 0.08223 -0.0297 0.0059 1.0000 9.000 0.7973 0.09106 0.08962 -0.0369 0.0059 1.0000 9.250 0.7947 0.09694 0.09548 -0.0410 0.0059 1.0000