XFOIL Version 6.94 Calculated polar for: NACA 64(3)-618 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.080 Re = 0.300 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- 0.500 0.5292 0.01308 0.00690 -0.1062 0.6309 0.6405 1.000 0.5862 0.01319 0.00698 -0.1069 0.6241 0.6459 1.500 0.6434 0.01324 0.00701 -0.1078 0.6173 0.6526 2.000 0.6993 0.01348 0.00725 -0.1083 0.6070 0.6637 2.500 0.7510 0.01414 0.00802 -0.1082 0.5997 0.6730 3.000 0.8029 0.01424 0.00821 -0.1077 0.5953 0.6831 3.500 0.8542 0.01455 0.00860 -0.1074 0.5901 0.6926 4.000 0.9054 0.01492 0.00905 -0.1072 0.5846 0.7013 4.500 0.9556 0.01503 0.00931 -0.1064 0.5777 0.7164 5.000 1.0078 0.01517 0.00954 -0.1059 0.5704 0.7295 5.500 1.0636 0.01531 0.00967 -0.1060 0.5591 0.7422 6.000 1.1111 0.01563 0.01009 -0.1049 0.5470 0.7557 6.500 1.1488 0.01505 0.00987 -0.1010 0.5336 0.7730 7.000 1.1880 0.01454 0.00927 -0.0974 0.5088 0.7892 7.500 1.2025 0.01452 0.00938 -0.0897 0.4898 0.8071 8.000 1.2102 0.01465 0.00965 -0.0808 0.4688 0.8304 8.500 1.2193 0.01522 0.01022 -0.0729 0.4466 0.8529 9.000 1.2124 0.01582 0.01106 -0.0624 0.4209 0.8905 9.500 1.1852 0.01694 0.01205 -0.0499 0.3745 0.9920 10.000 1.1676 0.02008 0.01494 -0.0428 0.3146 1.0000 10.500 1.1419 0.02395 0.01855 -0.0354 0.2613 1.0000 11.000 1.1210 0.02809 0.02247 -0.0295 0.2145 1.0000 11.500 1.1055 0.03247 0.02665 -0.0249 0.1710 1.0000 12.000 1.0930 0.03715 0.03120 -0.0214 0.1359 1.0000 12.500 1.0854 0.04181 0.03571 -0.0188 0.1068 1.0000 13.000 1.0860 0.04614 0.03997 -0.0171 0.0809 1.0000 13.500 1.0782 0.05145 0.04513 -0.0156 0.0589 1.0000 14.000 1.0731 0.05700 0.05060 -0.0147 0.0375 1.0000 14.500 1.0538 0.06448 0.05818 -0.0137 0.0239 1.0000 15.000 1.0462 0.07092 0.06501 -0.0126 0.0207 1.0000 15.500 1.0623 0.07502 0.06931 -0.0124 0.0202 1.0000 16.000 1.0782 0.07949 0.07401 -0.0127 0.0199 1.0000 16.500 1.0896 0.08485 0.07964 -0.0134 0.0198 1.0000 17.000 1.0936 0.09139 0.08657 -0.0148 0.0197 1.0000 17.500 1.0820 0.10039 0.09593 -0.0175 0.0196 1.0000 18.000 1.0625 0.11092 0.10684 -0.0215 0.0197 1.0000 18.500 1.0248 0.12494 0.12127 -0.0279 0.0198 1.0000 19.000 0.9634 0.14461 0.14137 -0.0382 0.0201 1.0000