Airfoil: CR-001 Builder: J. Robertson Comment: clean Number of Reynolds #'s: 4 Average Reynolds #: 60100 Number of angles of attack: 49 alpha / Cl / Cm -6.37 -0.332 -0.1200 -5.00 -0.226 -0.1200 -4.08 -0.107 -0.1200 -2.97 -0.002 -0.1200 -1.94 0.106 -0.1200 -0.84 0.209 -0.1200 0.22 0.321 -0.1200 1.07 0.406 -0.1200 2.21 0.553 -0.1200 3.28 0.720 -0.1200 4.21 0.862 -0.1200 5.38 0.956 -0.1200 6.35 1.035 -0.1200 7.30 1.107 -0.1200 8.44 1.165 -0.1200 9.36 1.210 -0.1200 10.46 1.250 -0.1200 11.33 1.268 -0.1200 12.37 1.140 -0.1200 13.21 1.147 -0.1200 14.21 1.114 -0.1200 15.25 1.087 -0.1200 16.37 1.081 -0.1200 17.32 1.110 -0.1200 18.25 1.115 -0.1200 16.88 1.114 -0.1200 15.85 1.119 -0.1200 14.86 1.107 -0.1200 13.81 1.101 -0.1200 12.90 1.152 -0.1200 11.98 1.271 -0.1200 10.93 1.262 -0.1200 9.98 1.231 -0.1200 8.97 1.182 -0.1200 7.83 1.128 -0.1200 6.83 1.060 -0.1200 5.80 0.983 -0.1200 4.76 0.896 -0.1200 3.76 0.784 -0.1200 2.76 0.626 -0.1200 1.76 0.506 -0.1200 0.74 0.378 -0.1200 -0.27 0.278 -0.1200 -1.45 0.162 -0.1200 -2.39 0.071 -0.1200 -3.40 -0.024 -0.1200 -4.48 -0.145 -0.1200 -5.55 -0.256 -0.1200 -6.48 -0.302 -0.1200 Tabulated from data in file CL00657.DAT & reduced using program Q02.00L Average Reynolds #: 100100 Number of angles of attack: 49 alpha / Cl / Cm -6.35 -0.366 -0.1200 -5.07 -0.284 -0.1200 -4.03 -0.130 -0.1200 -2.93 0.015 -0.1200 -2.06 0.110 -0.1200 -0.96 0.227 -0.1200 0.09 0.373 -0.1200 1.22 0.540 -0.1200 2.12 0.665 -0.1200 3.23 0.792 -0.1200 4.41 0.897 -0.1200 5.35 0.982 -0.1200 6.30 1.060 -0.1200 7.23 1.132 -0.1200 8.31 1.196 -0.1200 9.41 1.244 -0.1200 10.28 1.272 -0.1200 11.32 1.290 -0.1200 12.39 1.281 -0.1200 13.35 1.199 -0.1200 14.44 1.115 -0.1200 15.27 1.133 -0.1200 16.34 1.097 -0.1200 17.28 1.104 -0.1200 18.49 1.086 -0.1200 16.80 1.092 -0.1200 15.91 1.074 -0.1200 14.88 1.109 -0.1200 13.84 1.111 -0.1200 12.93 1.199 -0.1200 11.98 1.275 -0.1200 10.90 1.267 -0.1200 9.79 1.243 -0.1200 8.94 1.203 -0.1200 7.90 1.155 -0.1200 6.84 1.077 -0.1200 5.75 0.990 -0.1200 4.86 0.912 -0.1200 3.78 0.819 -0.1200 2.74 0.717 -0.1200 1.69 0.586 -0.1200 0.63 0.440 -0.1200 -0.43 0.276 -0.1200 -1.28 0.181 -0.1200 -2.51 0.051 -0.1200 -3.52 -0.063 -0.1200 -4.40 -0.188 -0.1200 -5.46 -0.314 -0.1200 -6.51 -0.368 -0.1200 Tabulated from data in file CL00659.DAT & reduced using program Q02.00L Average Reynolds #: 200300 Number of angles of attack: 49 alpha / Cl / Cm -6.42 -0.387 -0.1200 -4.93 -0.253 -0.1200 -3.98 -0.079 -0.1200 -2.99 0.068 -0.1200 -1.74 0.244 -0.1200 -0.85 0.376 -0.1200 0.11 0.493 -0.1200 1.27 0.613 -0.1200 2.28 0.711 -0.1200 3.28 0.809 -0.1200 4.28 0.902 -0.1200 5.20 0.986 -0.1200 6.48 1.092 -0.1200 7.46 1.160 -0.1200 8.43 1.214 -0.1200 9.39 1.259 -0.1200 10.31 1.287 -0.1200 11.33 1.296 -0.1200 12.39 1.273 -0.1200 13.43 1.254 -0.1200 14.30 1.202 -0.1200 15.25 1.175 -0.1200 16.17 1.137 -0.1200 17.32 1.100 -0.1200 18.27 1.097 -0.1200 16.60 1.110 -0.1200 15.71 1.168 -0.1200 14.65 1.208 -0.1200 13.80 1.250 -0.1200 12.92 1.263 -0.1200 11.85 1.291 -0.1200 10.88 1.295 -0.1200 9.86 1.271 -0.1200 8.78 1.224 -0.1200 7.74 1.166 -0.1200 6.87 1.109 -0.1200 5.89 1.033 -0.1200 4.67 0.925 -0.1200 3.66 0.831 -0.1200 2.64 0.728 -0.1200 1.59 0.632 -0.1200 0.61 0.534 -0.1200 -0.49 0.405 -0.1200 -1.52 0.266 -0.1200 -2.56 0.118 -0.1200 -3.65 -0.034 -0.1200 -4.46 -0.173 -0.1200 -5.49 -0.326 -0.1200 -6.50 -0.390 -0.1200 Tabulated from data in file CL00661.DAT & reduced using program Q02.00L Average Reynolds #: 300700 Number of angles of attack: 49 alpha / Cl / Cm -6.47 -0.387 -0.1200 -5.17 -0.216 -0.1200 -3.98 0.003 -0.1200 -3.10 0.130 -0.1200 -1.97 0.285 -0.1200 -1.02 0.390 -0.1200 0.01 0.490 -0.1200 1.18 0.610 -0.1200 2.23 0.717 -0.1200 3.21 0.814 -0.1200 4.25 0.915 -0.1200 5.16 0.997 -0.1200 6.46 1.104 -0.1200 7.29 1.163 -0.1200 8.51 1.240 -0.1200 9.60 1.296 -0.1200 10.36 1.317 -0.1200 11.35 1.322 -0.1200 12.52 1.299 -0.1200 13.31 1.275 -0.1200 13.97 1.291 -0.1200 15.08 1.232 -0.1200 16.00 1.170 -0.1200 17.05 1.139 -0.1200 18.06 1.122 -0.1200 16.93 1.133 -0.1200 15.94 1.182 -0.1200 15.01 1.235 -0.1200 14.11 1.298 -0.1200 13.11 1.280 -0.1200 11.92 1.309 -0.1200 10.78 1.316 -0.1200 9.76 1.291 -0.1200 8.77 1.244 -0.1200 7.70 1.176 -0.1200 6.78 1.111 -0.1200 5.63 1.022 -0.1200 4.54 0.928 -0.1200 3.77 0.855 -0.1200 2.57 0.738 -0.1200 1.70 0.651 -0.1200 0.58 0.534 -0.1200 -0.24 0.457 -0.1200 -1.44 0.335 -0.1200 -2.36 0.224 -0.1200 -3.44 0.075 -0.1200 -4.55 -0.099 -0.1200 -5.42 -0.270 -0.1200 -6.51 -0.393 -0.1200 Tabulated from data in file CL00663.DAT & reduced using program Q02.00L File cr001.lft created on 09-12-1997 at 13:46:17 using program FORMAT