Airfoil: S7075 (A) Builder: J. Robertson Comment: flap = 0 degs: clean Number of Reynolds #'s: 4 Average Reynolds #: 60200 Number of angles of attack: 49 alpha / Cl / Cm -5.99 -0.306 -0.0399 -4.73 -0.217 -0.0468 -3.74 -0.148 -0.0483 -2.83 -0.081 -0.0445 -1.54 0.023 -0.0479 -0.57 0.122 -0.0481 0.37 0.223 -0.0544 1.36 0.333 -0.0597 2.38 0.451 -0.0674 3.42 0.613 -0.0779 4.47 0.774 -0.0797 5.72 0.885 -0.0706 6.68 0.966 -0.0650 7.60 1.020 -0.0616 8.50 1.082 -0.0589 9.68 1.128 -0.0503 10.61 1.148 -0.0466 11.54 1.163 -0.0477 12.67 0.960 -0.0993 13.57 0.930 -0.1095 14.52 0.973 -0.1263 15.75 0.930 -0.1261 16.44 0.997 -0.1356 17.67 1.009 -0.1408 18.66 1.004 -0.1388 16.97 1.020 -0.1432 15.83 0.945 -0.1334 14.98 0.976 -0.1311 13.85 0.980 -0.1201 13.04 0.995 -0.1143 12.01 1.156 -0.0784 10.97 1.184 -0.0551 9.96 1.158 -0.0527 9.17 1.147 -0.0568 8.09 1.084 -0.0637 7.01 1.006 -0.0694 5.89 0.922 -0.0775 5.09 0.852 -0.0806 3.93 0.725 -0.0887 2.77 0.549 -0.0818 1.91 0.407 -0.0721 0.76 0.273 -0.0603 -0.28 0.171 -0.0547 -1.32 0.077 -0.0512 -2.35 -0.009 -0.0517 -3.39 -0.098 -0.0514 -4.43 -0.182 -0.0507 -5.22 -0.244 -0.0491 -6.39 -0.346 -0.0372 Tabulated from data in file CL01325.DAT & reduced using program Q06.01L Average Reynolds #: 100500 Number of angles of attack: 49 alpha / Cl / Cm -5.96 -0.387 -0.0312 -4.53 -0.229 -0.0496 -3.52 -0.136 -0.0530 -2.77 -0.068 -0.0542 -1.74 0.025 -0.0570 -0.70 0.143 -0.0591 0.36 0.306 -0.0718 1.41 0.449 -0.0812 2.46 0.590 -0.0864 3.53 0.707 -0.0858 4.61 0.809 -0.0804 5.66 0.895 -0.0746 6.71 0.975 -0.0708 7.75 1.060 -0.0690 8.74 1.117 -0.0635 9.79 1.165 -0.0578 10.78 1.207 -0.0520 11.77 1.232 -0.0475 12.69 1.178 -0.0693 13.58 1.038 -0.1265 14.61 1.024 -0.1348 15.64 1.011 -0.1392 16.68 0.975 -0.1381 17.78 1.027 -0.1458 18.51 1.030 -0.1460 16.86 1.017 -0.1504 15.89 0.980 -0.1443 14.93 0.992 -0.1407 14.05 1.051 -0.1406 12.87 1.166 -0.0898 11.99 1.236 -0.0530 10.89 1.206 -0.0530 10.02 1.171 -0.0576 8.89 1.117 -0.0633 7.99 1.072 -0.0676 7.10 1.003 -0.0709 5.93 0.911 -0.0731 4.98 0.840 -0.0789 3.77 0.734 -0.0860 2.82 0.633 -0.0917 1.91 0.513 -0.0885 0.73 0.356 -0.0805 -0.12 0.227 -0.0698 -1.31 0.059 -0.0577 -2.16 -0.005 -0.0600 -3.34 -0.115 -0.0544 -4.21 -0.194 -0.0527 -5.41 -0.311 -0.0497 -6.38 -0.424 -0.0258 Tabulated from data in file CL01319.DAT & reduced using program Q06.01L Average Reynolds #: 200800 Number of angles of attack: 49 alpha / Cl / Cm -5.85 -0.340 -0.0495 -4.72 -0.180 -0.0677 -3.62 -0.057 -0.0737 -2.46 0.067 -0.0792 -1.67 0.162 -0.0848 -0.49 0.285 -0.0850 0.62 0.415 -0.0863 1.46 0.501 -0.0846 2.62 0.624 -0.0842 3.60 0.738 -0.0828 4.72 0.840 -0.0802 5.51 0.908 -0.0783 6.63 1.001 -0.0752 7.69 1.080 -0.0714 8.72 1.139 -0.0657 9.75 1.189 -0.0591 10.82 1.227 -0.0531 11.82 1.243 -0.0480 12.50 1.241 -0.0466 13.59 1.141 -0.1454 14.74 1.114 -0.1579 15.50 1.020 -0.1598 16.65 1.002 -0.1585 17.81 1.026 -0.1643 18.60 1.039 -0.1649 16.65 0.995 -0.1601 15.78 1.006 -0.1616 15.01 1.022 -0.1570 13.91 1.082 -0.1523 12.86 1.160 -0.1214 11.97 1.240 -0.0506 11.08 1.229 -0.0542 9.89 1.190 -0.0608 9.03 1.151 -0.0656 8.11 1.105 -0.0707 6.83 1.020 -0.0767 5.82 0.942 -0.0797 4.78 0.853 -0.0826 3.74 0.755 -0.0847 2.84 0.650 -0.0866 1.77 0.534 -0.0874 0.71 0.425 -0.0889 -0.30 0.313 -0.0883 -1.32 0.207 -0.0901 -2.37 0.077 -0.0826 -3.37 -0.025 -0.0783 -4.37 -0.137 -0.0728 -5.36 -0.259 -0.0654 -6.41 -0.422 -0.0289 Tabulated from data in file CL01321.DAT & reduced using program Q06.01L Average Reynolds #: 301500 Number of angles of attack: 49 alpha / Cl / Cm -5.88 -0.250 -0.0788 -4.68 -0.112 -0.0869 -3.72 -0.016 -0.0885 -2.70 0.088 -0.0909 -1.61 0.196 -0.0928 -0.57 0.291 -0.0882 0.38 0.416 -0.0881 1.51 0.539 -0.0882 2.61 0.655 -0.0873 3.77 0.767 -0.0862 4.63 0.848 -0.0847 5.54 0.928 -0.0821 6.86 1.036 -0.0783 7.71 1.099 -0.0747 8.54 1.150 -0.0702 9.72 1.208 -0.0625 10.82 1.245 -0.0549 11.56 1.258 -0.0497 12.88 1.254 -0.0550 13.52 1.187 -0.1365 14.62 1.144 -0.1546 15.60 1.038 -0.1605 16.63 1.038 -0.1649 17.47 1.046 -0.1649 18.75 1.054 -0.1695 16.77 1.036 -0.1647 15.78 1.043 -0.1629 15.13 1.115 -0.1616 13.92 1.205 -0.1422 13.07 1.209 -0.1128 12.07 1.260 -0.0485 10.89 1.248 -0.0534 10.01 1.220 -0.0587 9.11 1.182 -0.0643 8.07 1.120 -0.0698 7.07 1.051 -0.0738 5.94 0.960 -0.0773 4.77 0.858 -0.0806 3.93 0.781 -0.0823 2.62 0.652 -0.0845 1.74 0.562 -0.0859 0.87 0.469 -0.0860 -0.30 0.335 -0.0859 -1.33 0.223 -0.0915 -2.47 0.107 -0.0911 -3.21 0.035 -0.0889 -4.33 -0.079 -0.0875 -5.36 -0.187 -0.0841 -6.37 -0.323 -0.0646 Tabulated from data in file CL01323.DAT & reduced using program Q06.01L File S7075A0.LFT created on 10-24-1997 at 19:34:41 using program FORMAT