Airfoil: RG15 (C) Builder: B. Champine Comment: flap = 2.5 degs Number of Reynolds #'s: 4 Average Reynolds #: 60038 Number of angles of attack: 57 alpha / Cl / Cm -8.99 -0.423 -0.0067 -8.08 -0.385 -0.0397 -7.04 -0.314 -0.0541 -6.09 -0.250 -0.0547 -5.03 -0.172 -0.0536 -3.71 -0.086 -0.0494 -2.97 -0.044 -0.0431 -1.96 0.049 -0.0509 -1.02 0.133 -0.0550 0.15 0.232 -0.0606 1.02 0.353 -0.0733 2.20 0.538 -0.0910 3.29 0.643 -0.0880 4.22 0.718 -0.0821 5.23 0.800 -0.0720 6.18 0.862 -0.0654 7.25 0.928 -0.0608 8.29 0.974 -0.0540 9.25 1.011 -0.0496 10.17 1.036 -0.0490 11.17 1.006 -0.0903 12.13 0.958 -0.1389 13.09 0.892 -0.1554 14.14 0.905 -0.1574 15.07 0.931 -0.1631 16.20 0.902 -0.1568 17.07 0.959 -0.1604 18.12 0.927 -0.1629 19.26 0.959 -0.1690 18.63 0.923 -0.1744 17.58 0.899 -0.1628 16.58 0.927 -0.1585 15.61 0.925 -0.1696 14.56 0.893 -0.1563 13.60 0.924 -0.1540 12.57 0.927 -0.1437 11.68 1.094 -0.1392 10.70 1.040 -0.0597 9.74 1.034 -0.0498 8.72 1.004 -0.0541 7.75 0.961 -0.0599 6.69 0.905 -0.0669 5.68 0.848 -0.0744 4.63 0.767 -0.0807 3.61 0.688 -0.0897 2.49 0.589 -0.0975 1.57 0.464 -0.0910 0.53 0.295 -0.0674 -0.58 0.196 -0.0554 -1.50 0.115 -0.0534 -2.52 0.021 -0.0453 -3.56 -0.052 -0.0486 -4.63 -0.116 -0.0548 -5.56 -0.188 -0.0525 -6.60 -0.268 -0.0525 -7.71 -0.350 -0.0455 -8.58 -0.412 -0.0157 Tabulated from data in file cl02373.dat & reduced using program C06.01 Average Reynolds #: 99938 Number of angles of attack: 57 alpha / Cl / Cm -8.98 -0.547 0.0135 -7.94 -0.504 -0.0286 -6.99 -0.398 -0.0547 -6.04 -0.304 -0.0552 -4.88 -0.194 -0.0552 -3.81 -0.085 -0.0583 -2.98 -0.023 -0.0523 -1.97 0.063 -0.0523 -0.94 0.166 -0.0573 0.03 0.310 -0.0747 1.06 0.455 -0.0852 2.21 0.554 -0.0755 3.17 0.667 -0.0783 4.16 0.755 -0.0731 5.19 0.844 -0.0692 6.32 0.941 -0.0652 7.18 0.981 -0.0587 8.27 1.023 -0.0516 9.31 1.063 -0.0458 10.28 1.084 -0.0426 11.22 1.044 -0.0677 12.10 1.060 -0.1493 13.25 1.012 -0.1590 14.16 0.936 -0.1632 15.26 0.931 -0.1663 16.24 0.964 -0.1594 17.10 0.928 -0.1675 18.19 0.960 -0.1725 19.18 0.986 -0.1778 18.63 0.976 -0.1728 17.55 0.964 -0.1772 16.60 0.990 -0.1756 15.61 0.946 -0.1657 14.58 0.952 -0.1626 13.60 0.937 -0.1653 12.61 0.969 -0.1663 11.67 1.081 -0.1386 10.69 1.156 -0.0903 9.72 1.073 -0.0438 8.72 1.048 -0.0496 7.73 1.004 -0.0554 6.70 0.964 -0.0627 5.72 0.906 -0.0685 4.63 0.813 -0.0714 3.64 0.725 -0.0762 2.58 0.611 -0.0805 1.55 0.510 -0.0845 0.57 0.399 -0.0854 -0.48 0.225 -0.0667 -1.47 0.113 -0.0550 -2.54 0.013 -0.0501 -3.60 -0.067 -0.0543 -4.54 -0.153 -0.0549 -5.61 -0.259 -0.0530 -6.67 -0.359 -0.0527 -7.64 -0.458 -0.0437 -8.62 -0.530 -0.0007 Tabulated from data in file cl02375.dat & reduced using program C06.01 Average Reynolds #: 199782 Number of angles of attack: 57 alpha / Cl / Cm -8.88 -0.524 -0.0004 -7.98 -0.438 -0.0473 -6.90 -0.309 -0.0709 -5.88 -0.222 -0.0693 -4.83 -0.122 -0.0691 -3.95 -0.037 -0.0703 -2.85 0.089 -0.0759 -1.85 0.206 -0.0796 -0.85 0.329 -0.0803 0.59 0.478 -0.0800 1.14 0.540 -0.0798 2.26 0.651 -0.0768 3.29 0.751 -0.0739 4.29 0.838 -0.0708 5.24 0.916 -0.0676 6.31 0.986 -0.0622 7.35 1.049 -0.0561 8.35 1.099 -0.0499 9.28 1.133 -0.0437 10.28 1.155 -0.0397 11.30 1.171 -0.1049 12.40 1.133 -0.1467 13.31 1.120 -0.1551 14.35 1.120 -0.1650 15.26 1.059 -0.1597 16.27 1.081 -0.1654 17.34 1.108 -0.1675 18.31 1.038 -0.1687 19.39 1.034 -0.1742 18.41 1.000 -0.1814 17.48 1.093 -0.1714 16.48 1.082 -0.1699 15.44 1.100 -0.1711 14.42 1.147 -0.1651 13.54 1.141 -0.1588 12.54 1.143 -0.1454 11.63 1.181 -0.1261 10.76 1.169 -0.0692 9.78 1.151 -0.0408 8.74 1.124 -0.0464 7.73 1.074 -0.0532 6.74 1.023 -0.0593 5.69 0.953 -0.0649 4.70 0.877 -0.0687 3.63 0.783 -0.0715 2.59 0.679 -0.0736 1.49 0.567 -0.0762 0.57 0.472 -0.0780 -0.67 0.341 -0.0790 -1.52 0.248 -0.0797 -2.54 0.124 -0.0750 -3.60 -0.002 -0.0707 -4.61 -0.102 -0.0681 -5.62 -0.201 -0.0676 -6.85 -0.305 -0.0707 -7.69 -0.402 -0.0591 -8.79 -0.521 -0.0055 Tabulated from data in file cl02377.dat & reduced using program C06.01 Average Reynolds #: 299742 Number of angles of attack: 59 alpha / Cl / Cm -8.86 -0.522 -0.0155 -8.02 -0.420 -0.0603 -7.04 -0.297 -0.0799 -6.08 -0.192 -0.0821 -5.07 -0.090 -0.0829 -4.00 0.017 -0.0843 -3.00 0.124 -0.0875 -1.89 0.242 -0.0862 -0.31 0.395 -0.0786 0.53 0.482 -0.0770 1.21 0.555 -0.0763 2.39 0.674 -0.0748 3.34 0.766 -0.0730 4.36 0.863 -0.0708 5.40 0.953 -0.0671 6.37 1.023 -0.0622 7.50 1.093 -0.0555 8.46 1.140 -0.0496 9.46 1.170 -0.0428 10.51 1.206 -0.0499 11.06 1.225 -0.0886 12.17 1.195 -0.1283 13.20 1.153 -0.1587 14.18 1.149 -0.1663 15.07 1.115 -0.1682 16.15 1.078 -0.1664 17.19 1.119 -0.1747 18.06 1.133 -0.1744 19.01 1.083 -0.1881 20.00 1.080 -0.2030 19.51 1.088 -0.1980 18.66 1.073 -0.1911 17.67 1.026 -0.1793 16.54 0.965 -0.1665 15.63 0.981 -0.1658 14.64 0.990 -0.1631 13.58 1.118 -0.1650 12.66 1.169 -0.1456 11.46 1.213 -0.0933 10.77 1.212 -0.0615 9.79 1.178 -0.0408 8.76 1.156 -0.0458 7.74 1.111 -0.0524 6.66 1.047 -0.0587 5.53 0.968 -0.0649 4.46 0.876 -0.0690 3.44 0.781 -0.0717 2.36 0.676 -0.0740 1.15 0.552 -0.0757 0.35 0.468 -0.0770 -0.91 0.341 -0.0804 -1.84 0.248 -0.0852 -2.74 0.157 -0.0876 -4.03 0.011 -0.0833 -5.01 -0.084 -0.0823 -6.16 -0.203 -0.0808 -6.78 -0.266 -0.0801 -7.91 -0.402 -0.0671 -8.79 -0.525 -0.0182 Tabulated from data in file pg02379.dat & reduced using program C06.01 File rg15cf2.lft created using program C06.01 on Mon Feb 02 15:11:35 1998