Airfoil: RG15 (C) Builder: B. Champine / J. Robertson Comment: covering over obechi: flap = 10 degs Number of Reynolds #'s: 4 Average Reynolds #: 60100 Number of angles of attack: 49 alpha / Cl / Cm -6.70 -0.096 -0.1300 -5.04 0.051 -0.1300 -4.09 0.104 -0.1300 -3.08 0.201 -0.1300 -2.11 0.305 -0.1300 -1.15 0.396 -0.1300 -0.16 0.479 -0.1300 1.15 0.648 -0.1300 1.96 0.815 -0.1300 2.99 0.967 -0.1300 4.26 1.064 -0.1300 5.19 1.092 -0.1300 6.15 1.132 -0.1300 7.15 1.162 -0.1300 8.16 1.202 -0.1300 9.16 1.231 -0.1300 10.10 1.240 -0.1300 11.06 1.186 -0.1300 12.08 1.154 -0.1300 13.26 1.083 -0.1300 14.15 1.107 -0.1300 15.08 1.120 -0.1300 16.02 1.109 -0.1300 17.27 1.111 -0.1300 18.04 1.129 -0.1300 16.56 1.133 -0.1300 15.53 1.140 -0.1300 14.48 1.145 -0.1300 13.43 1.146 -0.1300 12.62 1.136 -0.1300 11.59 1.139 -0.1300 10.64 1.216 -0.1300 9.44 1.260 -0.1300 8.61 1.231 -0.1300 7.56 1.196 -0.1300 6.45 1.164 -0.1300 5.55 1.130 -0.1300 4.40 1.082 -0.1300 3.63 1.034 -0.1300 2.32 0.900 -0.1300 1.54 0.738 -0.1300 0.51 0.579 -0.1300 -0.76 0.429 -0.1300 -1.79 0.318 -0.1300 -2.81 0.221 -0.1300 -3.71 0.123 -0.1300 -4.86 0.047 -0.1300 -5.82 -0.023 -0.1300 -6.81 -0.124 -0.1300 Tabulated from data in file CL00964.DAT & reduced using program Q02.00L Average Reynolds #: 100000 Number of angles of attack: 49 alpha / Cl / Cm -6.74 -0.089 -0.1300 -5.08 0.100 -0.1300 -4.10 0.147 -0.1300 -3.12 0.213 -0.1300 -2.10 0.317 -0.1300 -1.12 0.431 -0.1300 -0.09 0.559 -0.1300 0.93 0.712 -0.1300 1.95 0.894 -0.1300 3.25 1.006 -0.1300 3.96 1.054 -0.1300 5.28 1.122 -0.1300 5.96 1.144 -0.1300 7.30 1.192 -0.1300 8.27 1.228 -0.1300 9.06 1.250 -0.1300 10.01 1.236 -0.1300 11.11 1.243 -0.1300 12.13 1.091 -0.1300 13.08 1.093 -0.1300 14.15 1.071 -0.1300 15.08 1.066 -0.1300 16.08 1.078 -0.1300 17.09 1.094 -0.1300 18.22 1.097 -0.1300 16.33 1.068 -0.1300 15.37 1.085 -0.1300 14.49 1.072 -0.1300 13.43 1.095 -0.1300 12.61 1.122 -0.1300 11.55 1.138 -0.1300 10.46 1.229 -0.1300 9.66 1.258 -0.1300 8.56 1.224 -0.1300 7.64 1.193 -0.1300 6.55 1.148 -0.1300 5.46 1.112 -0.1300 4.60 1.074 -0.1300 3.48 1.002 -0.1300 2.41 0.935 -0.1300 1.32 0.779 -0.1300 0.46 0.621 -0.1300 -0.61 0.489 -0.1300 -1.64 0.364 -0.1300 -2.66 0.254 -0.1300 -3.72 0.157 -0.1300 -4.77 0.119 -0.1300 -5.87 -0.000 -0.1300 -6.90 -0.078 -0.1300 Tabulated from data in file CL00966.DAT & reduced using program Q02.00L Average Reynolds #: 200100 Number of angles of attack: 49 alpha / Cl / Cm -6.57 0.064 -0.1300 -5.08 0.193 -0.1300 -3.87 0.292 -0.1300 -2.97 0.365 -0.1300 -2.14 0.447 -0.1300 -1.04 0.546 -0.1300 0.05 0.731 -0.1300 1.00 0.855 -0.1300 2.09 0.947 -0.1300 3.13 1.022 -0.1300 4.22 1.089 -0.1300 5.00 1.125 -0.1300 6.25 1.179 -0.1300 7.16 1.220 -0.1300 8.28 1.260 -0.1300 9.13 1.280 -0.1300 10.09 1.289 -0.1300 10.99 1.273 -0.1300 12.11 1.178 -0.1300 13.05 1.151 -0.1300 14.32 1.108 -0.1300 15.10 1.084 -0.1300 16.12 1.100 -0.1300 17.29 1.109 -0.1300 18.11 1.097 -0.1300 16.26 1.069 -0.1300 15.42 1.082 -0.1300 14.45 1.103 -0.1300 13.36 1.126 -0.1300 12.50 1.167 -0.1300 11.47 1.242 -0.1300 10.52 1.284 -0.1300 9.55 1.296 -0.1300 8.52 1.259 -0.1300 7.50 1.224 -0.1300 6.57 1.185 -0.1300 5.36 1.132 -0.1300 4.37 1.086 -0.1300 3.39 1.028 -0.1300 2.42 0.960 -0.1300 1.42 0.885 -0.1300 0.38 0.776 -0.1300 -0.64 0.608 -0.1300 -1.68 0.488 -0.1300 -2.71 0.387 -0.1300 -3.75 0.287 -0.1300 -4.91 0.196 -0.1300 -5.91 0.110 -0.1300 -6.69 0.050 -0.1300 Tabulated from data in file CL00968.DAT & reduced using program Q02.00L Average Reynolds #: 300100 Number of angles of attack: 49 alpha / Cl / Cm -6.75 0.095 -0.1300 -5.24 0.246 -0.1300 -4.19 0.311 -0.1300 -3.05 0.389 -0.1300 -2.11 0.519 -0.1300 -1.10 0.664 -0.1300 0.11 0.788 -0.1300 1.07 0.869 -0.1300 2.05 0.945 -0.1300 3.10 1.018 -0.1300 4.17 1.081 -0.1300 5.31 1.142 -0.1300 6.23 1.188 -0.1300 7.29 1.233 -0.1300 8.06 1.260 -0.1300 9.09 1.298 -0.1300 10.03 1.307 -0.1300 11.31 1.296 -0.1300 12.10 1.243 -0.1300 13.01 1.164 -0.1300 14.04 1.123 -0.1300 14.87 1.087 -0.1300 15.85 1.079 -0.1300 17.01 1.077 -0.1300 17.86 1.125 -0.1300 16.51 1.089 -0.1300 15.63 1.072 -0.1300 14.48 1.098 -0.1300 13.60 1.142 -0.1300 12.52 1.191 -0.1300 11.64 1.283 -0.1300 10.65 1.319 -0.1300 9.50 1.319 -0.1300 8.46 1.272 -0.1300 7.40 1.236 -0.1300 6.40 1.193 -0.1300 5.36 1.144 -0.1300 4.23 1.084 -0.1300 3.39 1.034 -0.1300 2.53 0.979 -0.1300 1.38 0.890 -0.1300 0.27 0.798 -0.1300 -0.80 0.691 -0.1300 -1.56 0.610 -0.1300 -2.85 0.399 -0.1300 -3.94 0.324 -0.1300 -4.79 0.284 -0.1300 -5.73 0.193 -0.1300 -6.66 0.100 -0.1300 Tabulated from data in file CL00962.DAT & reduced using program Q02.00L File rg15cf10.lft created on 09-12-1997 at 13:46:18 using program FORMAT