Airfoil: E472 Builder: D. Stanley Comment: clean Number of Reynolds #'s: 5 Average Reynolds #: 101000 Number of angles of attack: 49 alpha / Cl / Cm -5.95 -0.593 -0.0038 -4.71 -0.476 -0.0028 -3.44 -0.353 0.0000 -2.53 -0.265 0.0021 -1.59 -0.185 0.0048 -0.66 -0.092 0.0055 0.62 0.093 -0.0024 1.57 0.205 -0.0066 2.53 0.290 -0.0050 3.49 0.378 -0.0031 4.48 0.465 -0.0011 5.78 0.575 0.0009 6.73 0.660 0.0020 7.67 0.738 0.0035 8.56 0.707 -0.0426 9.75 0.681 -0.0705 10.66 0.651 -0.0741 11.60 0.643 -0.0769 12.55 0.664 -0.0805 13.50 0.674 -0.0816 14.80 0.688 -0.0848 15.77 0.710 -0.0876 16.77 0.754 -0.0943 17.76 0.773 -0.0979 18.75 0.815 -0.1068 16.99 0.763 -0.1027 16.08 0.720 -0.0961 15.18 0.751 -0.1022 14.02 0.719 -0.0956 13.13 0.660 -0.0865 12.00 0.649 -0.0859 10.86 0.645 -0.0826 10.05 0.656 -0.0781 8.95 0.666 -0.0656 8.19 0.755 -0.0155 7.12 0.698 -0.0015 6.01 0.606 -0.0020 4.90 0.507 -0.0033 4.06 0.435 -0.0043 2.93 0.338 -0.0061 1.82 0.236 -0.0080 1.01 0.164 -0.0115 -0.10 -0.018 -0.0028 -1.20 -0.151 0.0065 -2.29 -0.238 0.0032 -3.10 -0.311 0.0009 -4.20 -0.421 -0.0008 -5.32 -0.527 -0.0029 -6.45 -0.635 -0.0044 Tabulated from data in file CL01073.DAT & reduced using program Q06.01L Average Reynolds #: 202200 Number of angles of attack: 49 alpha / Cl / Cm -5.99 -0.612 -0.0040 -4.66 -0.488 -0.0031 -3.65 -0.393 -0.0010 -2.64 -0.302 0.0012 -1.64 -0.152 -0.0061 -0.60 -0.030 -0.0088 0.43 0.050 -0.0033 1.42 0.146 -0.0010 2.39 0.280 -0.0069 3.75 0.412 -0.0053 4.43 0.475 -0.0037 5.70 0.598 -0.0007 6.68 0.688 0.0014 7.64 0.771 0.0032 8.57 0.854 0.0056 9.77 0.952 0.0085 10.67 1.022 0.0109 11.58 1.083 0.0135 12.34 0.680 -0.0915 13.63 0.695 -0.0925 14.63 0.708 -0.0939 15.64 0.716 -0.0948 16.66 0.742 -0.0989 17.65 0.755 -0.1005 18.62 0.773 -0.1022 17.03 0.754 -0.1034 16.03 0.727 -0.0989 15.04 0.711 -0.0974 14.05 0.689 -0.0939 13.07 0.681 -0.0929 11.79 0.675 -0.0933 10.88 0.681 -0.0903 9.94 0.694 -0.0845 9.06 0.724 -0.0682 7.99 0.802 0.0030 7.18 0.726 0.0013 6.07 0.628 -0.0011 4.95 0.523 -0.0025 4.10 0.443 -0.0046 2.93 0.334 -0.0069 2.05 0.236 -0.0054 0.92 0.092 -0.0006 -0.21 0.004 -0.0066 -1.08 -0.087 -0.0077 -2.22 -0.247 -0.0003 -3.36 -0.369 0.0012 -4.23 -0.449 -0.0004 -5.46 -0.562 -0.0029 -6.37 -0.641 -0.0045 Tabulated from data in file CL01075.DAT & reduced using program Q06.01L Average Reynolds #: 303100 Number of angles of attack: 49 alpha / Cl / Cm -5.99 -0.626 -0.0050 -4.55 -0.492 -0.0032 -3.47 -0.386 -0.0007 -2.42 -0.256 -0.0036 -1.74 -0.156 -0.0089 -0.31 -0.009 -0.0067 0.38 0.054 -0.0050 1.39 0.145 -0.0009 2.38 0.272 -0.0033 3.70 0.424 -0.0057 4.71 0.518 -0.0035 5.68 0.609 -0.0011 6.61 0.697 0.0006 7.52 0.780 0.0024 8.63 0.886 0.0044 9.73 0.988 0.0067 10.59 1.063 0.0088 11.68 1.147 0.0120 12.75 1.212 0.0155 13.82 1.250 0.0183 14.02 0.770 -0.1016 15.49 0.767 -0.1017 16.74 0.765 -0.0983 17.65 0.794 -0.1026 18.58 0.825 -0.1073 16.83 0.777 -0.1000 15.93 0.793 -0.1024 15.04 0.794 -0.1039 14.20 0.763 -0.1001 13.04 0.759 -0.0995 11.93 0.746 -0.0981 11.12 0.733 -0.0916 10.09 0.801 -0.0751 9.36 0.953 0.0048 8.19 0.845 0.0037 6.95 0.729 0.0013 5.94 0.631 -0.0012 4.87 0.531 -0.0037 4.06 0.458 -0.0055 2.91 0.348 -0.0077 1.82 0.196 -0.0004 0.99 0.112 -0.0026 -0.17 0.002 -0.0063 -1.09 -0.077 -0.0097 -2.28 -0.237 -0.0042 -3.17 -0.356 0.0006 -4.40 -0.472 -0.0019 -5.37 -0.570 -0.0040 -6.38 -0.657 -0.0062 Tabulated from data in file CL01077.DAT & reduced using program Q06.01L Average Reynolds #: 403500 Number of angles of attack: 46 alpha / Cl / Cm -4.72 -0.541 -0.0041 -3.71 -0.428 -0.0017 -2.68 -0.278 -0.0076 -1.64 -0.149 -0.0104 -0.44 -0.035 -0.0065 0.66 0.078 -0.0042 1.71 0.178 -0.0014 2.75 0.297 -0.0004 3.71 0.419 -0.0057 4.69 0.517 -0.0038 5.63 0.609 -0.0019 6.54 0.702 -0.0001 7.68 0.812 0.0016 8.52 0.893 0.0031 9.82 1.015 0.0061 10.60 1.082 0.0079 11.61 1.161 0.0107 12.79 1.236 0.0139 13.71 1.272 0.0165 14.56 1.262 -0.0090 14.80 0.806 -0.1003 16.55 0.838 -0.1048 17.52 0.847 -0.1047 18.51 0.899 -0.1083 17.09 0.875 -0.1070 16.12 0.845 -0.1031 14.91 0.822 -0.1007 14.17 0.809 -0.0990 13.00 0.775 -0.0951 12.06 0.794 -0.0929 11.24 0.851 -0.0823 10.86 1.102 0.0078 9.12 0.948 0.0063 8.23 0.868 0.0042 7.07 0.759 0.0023 5.97 0.644 -0.0001 5.03 0.561 -0.0022 4.01 0.463 -0.0047 2.99 0.332 -0.0021 1.92 0.208 -0.0005 0.78 0.099 -0.0037 -0.09 0.009 -0.0054 -1.04 -0.076 -0.0075 -2.38 -0.226 -0.0090 -3.33 -0.366 -0.0014 -4.32 -0.472 -0.0014 Tabulated from data in file CL01079.DAT & reduced using program Q06.01L Average Reynolds #: 504600 Number of angles of attack: 51 alpha / Cl / Cm -5.82 -0.646 -0.0071 -4.66 -0.535 -0.0050 -3.48 -0.406 -0.0045 -2.32 -0.248 -0.0099 -1.57 -0.168 -0.0088 -0.08 -0.022 -0.0051 0.78 0.061 -0.0035 1.60 0.144 -0.0021 3.01 0.278 0.0018 3.70 0.368 -0.0008 4.98 0.517 -0.0032 5.69 0.586 -0.0018 6.91 0.704 0.0008 8.07 0.818 0.0031 8.74 0.883 0.0045 9.83 0.989 0.0067 10.92 1.088 0.0094 12.01 1.179 0.0123 13.03 1.249 0.0154 13.99 1.297 0.0185 14.64 1.292 -0.0001 15.78 1.267 -0.0271 16.85 1.254 -0.0386 17.86 1.234 -0.0512 19.60 0.958 -0.1277 20.55 1.012 -0.1331 18.85 0.914 -0.1231 18.04 0.904 -0.1220 16.86 0.850 -0.1140 16.16 0.817 -0.1039 14.80 0.780 -0.1016 14.00 0.756 -0.0970 13.11 0.757 -0.0952 11.98 0.817 -0.0899 10.11 1.017 0.0081 8.95 0.904 0.0061 8.11 0.822 0.0038 6.72 0.687 0.0007 5.74 0.591 -0.0014 4.64 0.486 -0.0041 4.00 0.408 -0.0027 2.83 0.259 0.0013 1.52 0.135 -0.0027 0.76 0.057 -0.0039 -0.64 -0.084 -0.0062 -1.59 -0.178 -0.0089 -2.45 -0.272 -0.0095 -3.79 -0.457 -0.0020 -4.59 -0.538 -0.0032 -5.51 -0.626 -0.0047 -6.98 -0.764 -0.0073 Tabulated from data in file CL01855.DAT & reduced using program Q06.01L File E472.LFT created on 10-24-1997 at 19:34:41 using program FORMAT