Airfoil: S7075 (A) Builder: J. Robertson Comment: flap = 0 degs: Zig-Zag trip type "E" @ x/c = 58.3% (h = 0.017") Number of Reynolds #'s: 4 Average Reynolds #: 60700 Number of angles of attack: 49 alpha / Cl / Cm -5.84 -0.446 -0.0329 -4.57 -0.310 -0.0508 -3.66 -0.221 -0.0543 -2.76 -0.142 -0.0548 -1.47 -0.020 -0.0562 -0.58 0.070 -0.0577 0.31 0.175 -0.0570 1.60 0.327 -0.0669 2.51 0.439 -0.0728 3.45 0.570 -0.0842 4.80 0.746 -0.0896 5.72 0.843 -0.0854 6.63 0.910 -0.0758 7.55 0.977 -0.0672 8.83 1.069 -0.0614 9.71 1.106 -0.0562 10.58 1.144 -0.0490 11.82 1.172 -0.0456 12.65 1.051 -0.0807 13.89 0.976 -0.1123 14.80 0.983 -0.1355 15.70 0.949 -0.1410 16.62 0.963 -0.1424 17.53 1.026 -0.1563 18.87 1.042 -0.1615 16.82 0.989 -0.1477 15.96 0.952 -0.1419 14.78 0.953 -0.1358 13.99 0.956 -0.1343 12.94 1.173 -0.0713 11.83 1.168 -0.0506 11.04 1.161 -0.0506 9.93 1.114 -0.0558 8.83 1.067 -0.0612 8.04 1.017 -0.0669 6.87 0.936 -0.0748 5.69 0.839 -0.0829 4.85 0.765 -0.0909 3.63 0.601 -0.0913 2.78 0.490 -0.0835 1.62 0.352 -0.0741 0.80 0.257 -0.0685 -0.35 0.124 -0.0607 -1.47 0.009 -0.0593 -2.28 -0.066 -0.0614 -3.43 -0.184 -0.0596 -4.59 -0.300 -0.0602 -5.42 -0.389 -0.0572 -6.63 -0.497 -0.0337 Tabulated from data in file CL01805.DAT & reduced using program Q06.01L Average Reynolds #: 100600 Number of angles of attack: 49 alpha / Cl / Cm -5.91 -0.400 -0.0242 -4.60 -0.282 -0.0546 -3.69 -0.197 -0.0601 -2.76 -0.093 -0.0637 -1.42 0.076 -0.0693 -0.49 0.201 -0.0703 0.42 0.310 -0.0740 1.71 0.447 -0.0806 2.62 0.569 -0.0869 3.54 0.672 -0.0873 4.49 0.766 -0.0835 5.83 0.870 -0.0756 6.77 0.942 -0.0705 7.72 1.018 -0.0687 8.61 1.076 -0.0634 9.91 1.129 -0.0547 10.77 1.161 -0.0479 11.63 1.195 -0.0438 12.91 1.199 -0.0484 13.76 1.098 -0.1254 14.61 1.002 -0.1429 15.93 0.996 -0.1503 16.50 0.993 -0.1506 17.88 1.032 -0.1580 18.83 1.010 -0.1552 16.75 0.998 -0.1574 15.90 0.989 -0.1551 15.06 1.008 -0.1511 13.83 1.055 -0.1366 13.07 1.171 -0.0886 12.01 1.203 -0.0466 10.91 1.169 -0.0508 10.10 1.134 -0.0555 8.95 1.084 -0.0633 7.77 1.019 -0.0714 6.95 0.950 -0.0733 5.72 0.854 -0.0777 4.88 0.794 -0.0854 3.68 0.684 -0.0935 2.81 0.582 -0.0961 1.60 0.426 -0.0885 0.78 0.343 -0.0846 -0.39 0.203 -0.0780 -1.24 0.089 -0.0737 -2.41 -0.051 -0.0660 -3.26 -0.160 -0.0629 -4.44 -0.268 -0.0587 -5.62 -0.378 -0.0416 -6.45 -0.433 -0.0176 Tabulated from data in file CL01807.DAT & reduced using program Q06.01L Average Reynolds #: 201000 Number of angles of attack: 49 alpha / Cl / Cm -5.71 -0.293 -0.0683 -4.76 -0.168 -0.0823 -3.32 -0.022 -0.0863 -2.73 0.034 -0.0856 -1.29 0.174 -0.0861 -0.67 0.229 -0.0814 0.76 0.386 -0.0827 1.36 0.455 -0.0847 2.80 0.599 -0.0845 3.78 0.700 -0.0822 4.77 0.796 -0.0802 5.74 0.880 -0.0767 6.72 0.963 -0.0737 7.66 1.038 -0.0707 8.56 1.100 -0.0663 9.84 1.166 -0.0587 10.75 1.204 -0.0524 11.62 1.230 -0.0474 12.89 1.237 -0.0429 13.58 1.168 -0.1173 14.83 1.087 -0.1483 15.74 1.026 -0.1556 16.79 1.008 -0.1530 17.83 1.032 -0.1579 18.78 1.030 -0.1596 16.79 1.033 -0.1585 15.80 1.028 -0.1558 14.82 1.044 -0.1457 13.92 1.123 -0.1365 12.83 1.238 -0.0436 12.07 1.235 -0.0462 10.89 1.208 -0.0528 10.06 1.174 -0.0580 8.88 1.115 -0.0652 8.06 1.067 -0.0696 6.77 0.965 -0.0740 5.84 0.888 -0.0773 4.91 0.806 -0.0805 3.60 0.683 -0.0839 2.65 0.585 -0.0862 1.72 0.489 -0.0866 0.80 0.391 -0.0851 -0.54 0.242 -0.0835 -1.48 0.156 -0.0872 -2.43 0.065 -0.0861 -3.35 -0.023 -0.0854 -4.29 -0.120 -0.0851 -5.66 -0.284 -0.0717 -6.51 -0.410 -0.0295 Tabulated from data in file CL01809.DAT & reduced using program Q06.01L Average Reynolds #: 301400 Number of angles of attack: 49 alpha / Cl / Cm -5.85 -0.305 -0.0671 -4.57 -0.163 -0.0769 -3.67 -0.075 -0.0775 -2.33 0.060 -0.0792 -1.37 0.157 -0.0810 -0.40 0.250 -0.0785 0.55 0.364 -0.0804 1.50 0.468 -0.0808 2.52 0.576 -0.0807 3.57 0.684 -0.0797 4.71 0.797 -0.0781 5.83 0.895 -0.0753 6.92 0.987 -0.0720 7.96 1.070 -0.0681 8.97 1.136 -0.0632 9.94 1.190 -0.0587 10.89 1.227 -0.0526 11.82 1.251 -0.0472 12.72 1.258 -0.0431 13.40 1.229 -0.0809 14.71 1.151 -0.1440 15.74 1.066 -0.1594 16.86 1.048 -0.1605 17.60 1.032 -0.1592 18.71 1.047 -0.1644 16.58 1.051 -0.1621 15.75 1.041 -0.1580 14.96 1.128 -0.1481 13.84 1.199 -0.1154 13.36 1.251 -0.0465 11.80 1.251 -0.0490 10.98 1.229 -0.0538 9.73 1.178 -0.0618 8.88 1.127 -0.0652 7.99 1.069 -0.0694 6.59 0.955 -0.0740 6.05 0.909 -0.0756 4.51 0.775 -0.0799 3.95 0.718 -0.0799 2.80 0.603 -0.0812 1.70 0.488 -0.0813 0.65 0.375 -0.0811 -0.31 0.259 -0.0791 -1.29 0.164 -0.0819 -2.24 0.065 -0.0802 -3.25 -0.035 -0.0790 -4.69 -0.177 -0.0775 -5.25 -0.232 -0.0776 -6.56 -0.394 -0.0412 Tabulated from data in file CL01811.DAT & reduced using program Q06.01L File S7075A0T.LFT created on 10-24-1997 at 19:34:41 using program FORMAT