Airfoil: SG6040 Builder: M. Allen Comment: clean Number of Reynolds #'s: 6 Average Reynolds #: 100032 Number of angles of attack: 59 alpha / Cl / Cm -8.59 -0.628 -0.0543 -7.45 -0.586 -0.0503 -6.68 -0.530 -0.0520 -5.72 -0.445 -0.0572 -4.75 -0.324 -0.0689 -3.71 -0.190 -0.0758 -2.67 -0.142 -0.0618 -1.64 -0.046 -0.0600 -0.58 0.060 -0.0590 0.97 0.170 -0.0590 1.18 0.188 -0.0578 2.31 0.293 -0.0619 3.47 0.385 -0.0675 4.24 0.438 -0.0725 5.27 0.602 -0.0787 6.53 0.900 -0.0784 7.42 1.001 -0.0791 8.39 1.085 -0.0781 9.48 1.168 -0.0768 10.43 1.232 -0.0738 11.42 1.258 -0.0620 12.61 1.273 -0.0522 13.40 1.268 -0.0465 14.55 1.293 -0.0425 15.47 1.282 -0.0423 16.28 0.939 -0.1310 17.33 0.898 -0.1447 18.35 0.967 -0.1449 19.27 0.925 -0.1428 20.37 0.950 -0.1546 19.65 1.015 -0.1637 18.62 0.975 -0.1592 17.64 0.947 -0.1473 16.57 0.894 -0.1360 15.65 0.906 -0.1306 14.70 0.931 -0.1354 13.92 1.267 -0.0551 12.90 1.288 -0.0534 11.86 1.261 -0.0596 10.67 1.254 -0.0724 9.83 1.223 -0.0781 8.78 1.145 -0.0780 7.83 1.067 -0.0790 6.78 0.964 -0.0791 5.74 0.821 -0.0773 4.60 0.485 -0.0734 3.63 0.429 -0.0679 2.65 0.335 -0.0611 1.59 0.236 -0.0554 0.59 0.197 -0.0576 -0.51 0.077 -0.0541 -1.55 -0.031 -0.0552 -2.45 -0.123 -0.0562 -3.64 -0.169 -0.0708 -4.54 -0.282 -0.0645 -5.56 -0.402 -0.0496 -6.55 -0.500 -0.0413 -7.63 -0.582 -0.0380 -8.61 -0.618 -0.0417 Tabulated from data in file pg02398.dat & reduced using program C06.01 Average Reynolds #: 149935 Number of angles of attack: 59 alpha / Cl / Cm -8.86 -0.657 -0.0461 -7.81 -0.594 -0.0467 -6.69 -0.481 -0.0573 -5.84 -0.362 -0.0708 -4.77 -0.220 -0.0843 -3.66 -0.080 -0.0882 -2.82 0.013 -0.0874 -1.74 0.128 -0.0821 -0.69 0.222 -0.0777 0.54 0.327 -0.0739 1.82 0.439 -0.0727 2.35 0.493 -0.0724 3.73 0.625 -0.0718 4.40 0.694 -0.0712 5.43 0.805 -0.0701 6.44 0.927 -0.0770 7.47 1.037 -0.0788 8.50 1.131 -0.0777 9.50 1.207 -0.0748 10.65 1.261 -0.0655 11.57 1.261 -0.0557 12.48 1.285 -0.0500 13.75 1.312 -0.0440 14.52 1.319 -0.0420 15.65 1.333 -0.0423 16.51 1.318 -0.0450 17.26 0.902 -0.1404 18.56 0.917 -0.1562 19.53 0.974 -0.1603 20.48 0.972 -0.1658 19.51 0.889 -0.1702 18.34 0.918 -0.1612 17.49 0.909 -0.1519 16.31 0.888 -0.1524 15.40 0.909 -0.1450 14.78 1.327 -0.0477 13.80 1.315 -0.0473 12.79 1.301 -0.0522 11.82 1.274 -0.0583 10.78 1.269 -0.0680 9.71 1.234 -0.0778 8.65 1.147 -0.0810 7.66 1.059 -0.0820 6.71 0.966 -0.0807 5.69 0.839 -0.0736 4.50 0.722 -0.0732 3.63 0.631 -0.0738 2.61 0.522 -0.0741 1.60 0.426 -0.0737 0.35 0.317 -0.0759 -0.50 0.249 -0.0777 -1.51 0.156 -0.0822 -2.51 0.057 -0.0865 -3.77 -0.088 -0.0881 -4.65 -0.198 -0.0844 -5.91 -0.368 -0.0685 -6.72 -0.481 -0.0558 -7.82 -0.594 -0.0442 -8.92 -0.653 -0.0448 Tabulated from data in file cf02401.dat & reduced using program C06.01 Average Reynolds #: 199981 Number of angles of attack: 59 alpha / Cl / Cm -8.80 -0.665 -0.0503 -7.79 -0.535 -0.0636 -6.67 -0.377 -0.0810 -5.76 -0.262 -0.0900 -4.67 -0.142 -0.0930 -3.54 -0.035 -0.0900 -2.73 0.043 -0.0871 -1.71 0.141 -0.0844 -0.54 0.258 -0.0820 0.32 0.349 -0.0820 1.28 0.453 -0.0818 2.28 0.551 -0.0817 3.40 0.665 -0.0818 4.34 0.753 -0.0809 5.40 0.854 -0.0787 6.37 0.939 -0.0757 7.34 1.056 -0.0794 8.41 1.159 -0.0786 9.35 1.231 -0.0742 10.56 1.273 -0.0636 11.43 1.280 -0.0544 12.65 1.300 -0.0467 13.78 1.325 -0.0427 14.42 1.333 -0.0415 15.58 1.353 -0.0433 16.45 1.353 -0.0465 17.44 1.338 -0.0529 18.50 0.876 -0.1512 19.82 0.939 -0.1708 20.44 1.009 -0.1728 19.32 0.918 -0.1589 18.43 0.889 -0.1553 17.45 0.883 -0.1418 16.43 0.889 -0.1415 15.56 0.865 -0.1398 14.80 1.345 -0.0424 13.89 1.330 -0.0426 12.71 1.306 -0.0457 11.90 1.288 -0.0504 10.84 1.273 -0.0587 9.87 1.255 -0.0687 8.77 1.185 -0.0752 7.80 1.096 -0.0763 6.70 0.976 -0.0740 5.75 0.881 -0.0740 4.63 0.778 -0.0772 3.59 0.683 -0.0786 2.53 0.579 -0.0788 1.60 0.482 -0.0785 0.42 0.358 -0.0791 -0.54 0.259 -0.0796 -1.63 0.148 -0.0817 -2.71 0.041 -0.0850 -3.61 -0.045 -0.0879 -4.68 -0.147 -0.0905 -5.73 -0.260 -0.0878 -6.76 -0.389 -0.0766 -7.72 -0.524 -0.0620 -8.67 -0.644 -0.0482 Tabulated from data in file cf02404.dat & reduced using program C06.01 Average Reynolds #: 300055 Number of angles of attack: 59 alpha / Cl / Cm -8.96 -0.608 -0.0729 -8.06 -0.480 -0.0856 -7.10 -0.366 -0.0938 -5.92 -0.264 -0.0937 -4.95 -0.177 -0.0925 -3.94 -0.082 -0.0910 -2.94 0.020 -0.0904 -1.72 0.149 -0.0896 -0.79 0.249 -0.0894 0.23 0.358 -0.0892 1.39 0.484 -0.0888 2.42 0.597 -0.0888 3.35 0.694 -0.0888 4.64 0.824 -0.0880 5.49 0.913 -0.0867 6.51 1.013 -0.0838 7.69 1.118 -0.0804 8.60 1.191 -0.0775 9.59 1.246 -0.0701 10.48 1.275 -0.0616 11.45 1.286 -0.0525 12.64 1.312 -0.0456 13.43 1.326 -0.0438 14.43 1.345 -0.0441 15.55 1.371 -0.0463 16.48 1.382 -0.0487 17.47 1.386 -0.0537 18.47 1.384 -0.0580 19.52 1.380 -0.0695 20.07 0.989 -0.1857 19.72 0.939 -0.1789 18.70 0.904 -0.1636 17.42 0.864 -0.1529 16.50 0.884 -0.1472 16.16 1.380 -0.0482 14.77 1.356 -0.0438 13.85 1.340 -0.0427 12.87 1.321 -0.0441 11.84 1.300 -0.0488 10.82 1.287 -0.0562 9.83 1.264 -0.0655 8.79 1.209 -0.0744 7.71 1.124 -0.0778 6.61 1.030 -0.0821 5.68 0.939 -0.0851 4.47 0.817 -0.0873 2.82 0.643 -0.0882 2.58 0.615 -0.0882 1.35 0.485 -0.0888 0.33 0.373 -0.0884 -0.58 0.272 -0.0882 -1.59 0.165 -0.0886 -2.67 0.050 -0.0891 -3.80 -0.065 -0.0898 -4.69 -0.151 -0.0903 -5.76 -0.246 -0.0919 -6.55 -0.311 -0.0933 -7.62 -0.420 -0.0898 -8.68 -0.568 -0.0768 Tabulated from data in file cf02407.dat & reduced using program C06.01 Average Reynolds #: 399673 Number of angles of attack: 59 alpha / Cl / Cm -9.02 -0.570 -0.0869 -8.03 -0.453 -0.0948 -7.06 -0.369 -0.0944 -5.89 -0.271 -0.0927 -5.03 -0.186 -0.0918 -3.99 -0.087 -0.0921 -2.99 0.018 -0.0918 -1.93 0.134 -0.0913 -0.91 0.247 -0.0909 0.14 0.363 -0.0906 1.20 0.484 -0.0909 2.25 0.596 -0.0915 3.24 0.702 -0.0919 4.48 0.837 -0.0915 5.25 0.918 -0.0907 6.26 1.020 -0.0891 7.57 1.132 -0.0831 8.52 1.198 -0.0773 9.78 1.256 -0.0666 10.59 1.279 -0.0595 11.73 1.304 -0.0511 12.70 1.325 -0.0477 13.44 1.341 -0.0473 14.44 1.365 -0.0490 15.49 1.384 -0.0508 16.65 1.394 -0.0564 17.65 1.416 -0.0582 18.64 1.400 -0.0637 19.60 1.404 -0.0716 20.73 1.401 -0.0799 19.81 1.408 -0.0740 18.89 1.402 -0.0664 17.79 1.400 -0.0600 16.83 1.384 -0.0552 15.88 1.392 -0.0514 14.87 1.373 -0.0478 13.92 1.356 -0.0456 12.87 1.335 -0.0439 11.88 1.313 -0.0466 10.70 1.285 -0.0538 9.79 1.261 -0.0620 8.71 1.213 -0.0715 7.75 1.149 -0.0777 6.27 1.023 -0.0846 5.58 0.956 -0.0863 4.56 0.846 -0.0877 3.60 0.747 -0.0892 2.61 0.639 -0.0898 1.63 0.534 -0.0906 0.59 0.414 -0.0901 -0.48 0.301 -0.0908 -1.67 0.166 -0.0908 -2.56 0.064 -0.0906 -3.49 -0.036 -0.0901 -4.55 -0.144 -0.0900 -5.54 -0.237 -0.0900 -6.58 -0.328 -0.0908 -7.63 -0.412 -0.0924 -8.63 -0.519 -0.0891 Tabulated from data in file cf02409.dat & reduced using program C06.01 Average Reynolds #: 499595 Number of angles of attack: 53 alpha / Cl / Cm -6.01 -0.291 -0.0918 -4.99 -0.189 -0.0917 -4.00 -0.089 -0.0919 -2.93 0.030 -0.0907 -1.95 0.143 -0.0903 -0.90 0.262 -0.0906 0.11 0.376 -0.0910 1.13 0.495 -0.0908 2.17 0.610 -0.0908 3.24 0.727 -0.0902 4.27 0.841 -0.0896 5.28 0.946 -0.0884 6.59 1.073 -0.0850 7.38 1.142 -0.0816 8.61 1.214 -0.0712 10.01 1.270 -0.0598 11.02 1.301 -0.0530 11.77 1.311 -0.0484 12.84 1.339 -0.0476 13.81 1.363 -0.0494 14.65 1.374 -0.0511 15.84 1.387 -0.0545 16.89 1.391 -0.0586 18.31 1.404 -0.0651 18.31 1.398 -0.0658 19.71 1.406 -0.0727 20.73 1.422 -0.0809 19.62 1.403 -0.0736 18.70 1.409 -0.0667 17.88 1.387 -0.0620 16.84 1.396 -0.0571 15.84 1.395 -0.0532 14.81 1.380 -0.0491 13.82 1.363 -0.0467 12.87 1.340 -0.0425 11.72 1.316 -0.0439 10.46 1.285 -0.0512 9.80 1.269 -0.0563 8.46 1.206 -0.0688 7.23 1.130 -0.0787 6.44 1.064 -0.0826 5.49 0.972 -0.0856 4.57 0.874 -0.0869 3.70 0.784 -0.0879 2.69 0.672 -0.0873 1.60 0.554 -0.0893 0.64 0.442 -0.0894 -0.44 0.325 -0.0896 -1.54 0.194 -0.0894 -2.44 0.087 -0.0897 -3.54 -0.039 -0.0893 -4.55 -0.147 -0.0890 -5.63 -0.257 -0.0884 Tabulated from data in file cf02412.dat & reduced using program C06.01 File sg6040.lft created using program C06.01 on Mon Feb 02 15:11:35 1998