Airfoil: RG15 (C) Builder: B. Champine / J. Robertson Comment: covering over obechi: flap = 5 degs Number of Reynolds #'s: 4 Average Reynolds #: 60400 Number of angles of attack: 49 alpha / Cl / Cm -6.66 -0.206 -0.1100 -5.05 -0.068 -0.1100 -4.08 -0.006 -0.1100 -3.11 0.054 -0.1100 -2.09 0.161 -0.1100 -1.08 0.266 -0.1100 -0.08 0.359 -0.1100 0.85 0.463 -0.1100 2.12 0.704 -0.1100 3.05 0.813 -0.1100 4.02 0.888 -0.1100 5.03 0.957 -0.1100 6.05 1.002 -0.1100 7.10 1.037 -0.1100 8.23 1.086 -0.1100 9.21 1.114 -0.1100 10.16 1.104 -0.1100 11.08 1.084 -0.1100 12.03 1.043 -0.1100 13.23 1.033 -0.1100 14.20 1.008 -0.1100 15.16 1.003 -0.1100 16.24 0.983 -0.1100 17.18 0.965 -0.1100 18.12 0.945 -0.1100 16.55 0.998 -0.1100 15.51 1.018 -0.1100 14.51 1.071 -0.1100 13.47 1.047 -0.1100 12.48 1.095 -0.1100 11.47 1.120 -0.1100 10.60 1.166 -0.1100 9.61 1.170 -0.1100 8.57 1.141 -0.1100 7.49 1.097 -0.1100 6.64 1.070 -0.1100 5.50 1.008 -0.1100 4.55 0.953 -0.1100 3.51 0.875 -0.1100 2.38 0.763 -0.1100 1.43 0.595 -0.1100 0.36 0.427 -0.1100 -0.63 0.335 -0.1100 -1.63 0.237 -0.1100 -2.62 0.131 -0.1100 -3.65 0.041 -0.1100 -4.70 -0.033 -0.1100 -5.68 -0.119 -0.1100 -6.65 -0.208 -0.1100 Tabulated from data in file CL00952.DAT & reduced using program Q02.00L Average Reynolds #: 100200 Number of angles of attack: 49 alpha / Cl / Cm -6.79 -0.258 -0.1100 -5.23 -0.120 -0.1100 -4.23 -0.027 -0.1100 -3.24 0.038 -0.1100 -2.22 0.137 -0.1100 -0.95 0.280 -0.1100 0.00 0.423 -0.1100 0.98 0.600 -0.1100 2.10 0.741 -0.1100 2.92 0.816 -0.1100 4.18 0.913 -0.1100 5.00 0.975 -0.1100 6.11 1.046 -0.1100 7.11 1.081 -0.1100 8.20 1.130 -0.1100 9.15 1.166 -0.1100 10.09 1.189 -0.1100 11.25 1.157 -0.1100 11.96 1.082 -0.1100 13.22 1.072 -0.1100 14.13 1.012 -0.1100 15.22 0.972 -0.1100 16.15 0.958 -0.1100 17.11 0.975 -0.1100 18.08 0.966 -0.1100 16.45 0.961 -0.1100 15.59 0.970 -0.1100 14.55 1.010 -0.1100 13.52 1.064 -0.1100 12.48 1.066 -0.1100 11.50 1.143 -0.1100 10.60 1.152 -0.1100 9.63 1.183 -0.1100 8.63 1.132 -0.1100 7.53 1.093 -0.1100 6.49 1.054 -0.1100 5.59 1.010 -0.1100 4.57 0.934 -0.1100 3.48 0.849 -0.1100 2.46 0.763 -0.1100 1.42 0.650 -0.1100 0.38 0.485 -0.1100 -0.63 0.313 -0.1100 -1.63 0.195 -0.1100 -2.80 0.071 -0.1100 -3.64 0.007 -0.1100 -4.75 -0.080 -0.1100 -5.85 -0.182 -0.1100 -6.76 -0.258 -0.1100 Tabulated from data in file CL00955.DAT & reduced using program Q02.00L Average Reynolds #: 200600 Number of angles of attack: 49 alpha / Cl / Cm -6.82 -0.128 -0.1100 -4.95 0.048 -0.1100 -4.11 0.115 -0.1100 -3.00 0.200 -0.1100 -1.93 0.304 -0.1100 -0.86 0.433 -0.1100 -0.13 0.525 -0.1100 0.97 0.649 -0.1100 2.06 0.751 -0.1100 3.12 0.848 -0.1100 4.18 0.936 -0.1100 5.22 1.012 -0.1100 6.10 1.064 -0.1100 7.20 1.120 -0.1100 8.07 1.157 -0.1100 9.21 1.194 -0.1100 10.19 1.225 -0.1100 11.02 1.212 -0.1100 12.00 1.190 -0.1100 13.24 1.115 -0.1100 14.09 1.060 -0.1100 15.25 1.004 -0.1100 16.24 0.980 -0.1100 17.09 0.987 -0.1100 18.08 1.010 -0.1100 16.28 0.983 -0.1100 15.34 0.985 -0.1100 14.61 1.021 -0.1100 13.35 1.075 -0.1100 12.52 1.120 -0.1100 11.62 1.190 -0.1100 10.64 1.218 -0.1100 9.43 1.195 -0.1100 8.69 1.174 -0.1100 7.53 1.129 -0.1100 6.61 1.083 -0.1100 5.43 1.016 -0.1100 4.49 0.952 -0.1100 3.31 0.855 -0.1100 2.36 0.771 -0.1100 1.39 0.678 -0.1100 0.46 0.581 -0.1100 -0.60 0.462 -0.1100 -1.83 0.304 -0.1100 -2.81 0.218 -0.1100 -3.70 0.134 -0.1100 -4.73 0.056 -0.1100 -5.74 -0.029 -0.1100 -6.76 -0.119 -0.1100 Tabulated from data in file CL00957.DAT & reduced using program Q02.00L Average Reynolds #: 300500 Number of angles of attack: 49 alpha / Cl / Cm -6.86 -0.131 -0.1100 -4.98 0.053 -0.1100 -4.16 0.135 -0.1100 -2.94 0.255 -0.1100 -1.88 0.365 -0.1100 -1.10 0.442 -0.1100 -0.04 0.543 -0.1100 1.12 0.657 -0.1100 2.06 0.748 -0.1100 3.10 0.846 -0.1100 4.16 0.933 -0.1100 5.22 1.012 -0.1100 6.18 1.072 -0.1100 7.20 1.124 -0.1100 8.24 1.170 -0.1100 9.25 1.203 -0.1100 10.22 1.240 -0.1100 11.03 1.230 -0.1100 12.22 1.196 -0.1100 13.11 1.147 -0.1100 14.13 1.059 -0.1100 15.09 1.005 -0.1100 16.12 0.990 -0.1100 17.08 1.066 -0.1100 17.92 1.087 -0.1100 16.31 1.011 -0.1100 15.56 0.995 -0.1100 14.35 1.050 -0.1100 13.47 1.130 -0.1100 12.54 1.208 -0.1100 11.35 1.240 -0.1100 10.64 1.236 -0.1100 9.38 1.197 -0.1100 8.63 1.178 -0.1100 7.41 1.132 -0.1100 6.41 1.082 -0.1100 5.38 1.024 -0.1100 4.35 0.948 -0.1100 3.32 0.866 -0.1100 2.24 0.767 -0.1100 1.17 0.650 -0.1100 0.40 0.566 -0.1100 -0.74 0.449 -0.1100 -1.60 0.361 -0.1100 -2.77 0.245 -0.1100 -3.79 0.152 -0.1100 -4.92 0.043 -0.1100 -5.76 -0.032 -0.1100 -6.99 -0.146 -0.1100 Tabulated from data in file CL00960.DAT & reduced using program Q02.00L File rg15cf5.lft created on 09-12-1997 at 13:46:18 using program FORMAT