Airfoil: Davis 3R Builder: H. Cole Comment: multiple plain trips (h/c = 0.15%; w/c = 2.1%) @ x/c = 28.1%; 42.4%; 54.4%; 65.4%; 76.3% Number of Reynolds #'s: 5 Average Reynolds #: 39800 Number of angles of attack: 49 alpha / Cl / Cm -3.18 -0.167 -0.1700 -1.63 0.187 -0.1700 -0.72 0.314 -0.1700 0.40 0.446 -0.1700 1.31 0.551 -0.1700 2.38 0.669 -0.1700 3.50 0.781 -0.1700 4.39 0.845 -0.1700 5.50 0.926 -0.1700 6.44 1.075 -0.1700 7.55 1.147 -0.1700 8.45 1.184 -0.1700 9.54 1.217 -0.1700 10.62 1.262 -0.1700 11.70 1.304 -0.1700 12.53 1.312 -0.1700 13.56 1.324 -0.1700 14.55 1.295 -0.1700 15.53 1.268 -0.1700 16.50 1.244 -0.1700 17.47 1.171 -0.1700 18.45 1.162 -0.1700 19.66 1.134 -0.1700 20.52 1.143 -0.1700 21.46 1.176 -0.1700 19.99 1.165 -0.1700 19.07 1.150 -0.1700 17.88 1.124 -0.1700 17.01 1.127 -0.1700 16.08 1.155 -0.1700 14.91 1.225 -0.1700 14.01 1.284 -0.1700 13.11 1.283 -0.1700 11.95 1.275 -0.1700 11.02 1.245 -0.1700 10.06 1.204 -0.1700 9.08 1.168 -0.1700 8.07 1.121 -0.1700 7.09 1.077 -0.1700 5.84 0.939 -0.1700 4.90 0.838 -0.1700 3.97 0.734 -0.1700 2.76 0.647 -0.1700 1.83 0.549 -0.1700 0.91 0.430 -0.1700 -0.29 0.291 -0.1700 -1.18 0.176 -0.1700 -2.15 -0.000 -0.1700 -3.29 -0.223 -0.1700 Tabulated from data in file CL00751.DAT & reduced using program Q02.00L Average Reynolds #: 59600 Number of angles of attack: 49 alpha / Cl / Cm -3.14 -0.026 -0.1700 -1.58 0.262 -0.1700 -0.59 0.396 -0.1700 0.36 0.510 -0.1700 1.48 0.646 -0.1700 2.37 0.746 -0.1700 3.46 0.854 -0.1700 4.59 0.951 -0.1700 5.54 1.042 -0.1700 6.45 1.099 -0.1700 7.51 1.156 -0.1700 8.56 1.180 -0.1700 9.50 1.222 -0.1700 10.62 1.270 -0.1700 11.70 1.310 -0.1700 12.57 1.323 -0.1700 13.64 1.310 -0.1700 14.47 1.271 -0.1700 15.57 1.146 -0.1700 16.46 1.062 -0.1700 17.53 1.106 -0.1700 18.59 1.141 -0.1700 19.72 1.155 -0.1700 20.46 1.138 -0.1700 21.56 1.176 -0.1700 20.02 1.153 -0.1700 18.99 1.132 -0.1700 17.99 1.124 -0.1700 17.01 1.121 -0.1700 16.05 1.141 -0.1700 15.09 1.242 -0.1700 14.13 1.288 -0.1700 13.07 1.334 -0.1700 12.06 1.322 -0.1700 11.06 1.286 -0.1700 10.06 1.243 -0.1700 9.03 1.193 -0.1700 8.00 1.155 -0.1700 6.98 1.123 -0.1700 6.00 1.057 -0.1700 4.99 0.970 -0.1700 3.97 0.878 -0.1700 2.95 0.780 -0.1700 1.93 0.676 -0.1700 0.93 0.576 -0.1700 -0.33 0.413 -0.1700 -1.25 0.302 -0.1700 -2.21 0.144 -0.1700 -3.23 -0.039 -0.1700 Tabulated from data in file CL00753.DAT & reduced using program Q02.00L Average Reynolds #: 99800 Number of angles of attack: 49 alpha / Cl / Cm -3.11 0.105 -0.1700 -1.56 0.382 -0.1700 -0.53 0.502 -0.1700 0.51 0.610 -0.1700 1.51 0.712 -0.1700 2.52 0.810 -0.1700 3.50 0.903 -0.1700 4.47 0.993 -0.1700 5.67 1.092 -0.1700 6.66 1.145 -0.1700 7.66 1.188 -0.1700 8.64 1.233 -0.1700 9.61 1.278 -0.1700 10.53 1.316 -0.1700 11.72 1.353 -0.1700 12.59 1.365 -0.1700 13.69 1.328 -0.1700 14.61 1.279 -0.1700 15.67 1.168 -0.1700 16.63 1.160 -0.1700 17.69 1.150 -0.1700 18.68 1.152 -0.1700 19.43 1.169 -0.1700 20.49 1.179 -0.1700 21.53 1.193 -0.1700 20.05 1.176 -0.1700 18.76 1.163 -0.1700 17.98 1.169 -0.1700 16.86 1.153 -0.1700 16.10 1.174 -0.1700 14.88 1.210 -0.1700 13.92 1.367 -0.1700 12.97 1.352 -0.1700 12.10 1.346 -0.1700 10.94 1.311 -0.1700 9.89 1.269 -0.1700 9.10 1.230 -0.1700 7.96 1.174 -0.1700 6.88 1.124 -0.1700 5.81 1.069 -0.1700 5.01 1.013 -0.1700 3.88 0.909 -0.1700 2.80 0.801 -0.1700 1.98 0.723 -0.1700 0.84 0.618 -0.1700 -0.26 0.501 -0.1700 -1.33 0.390 -0.1700 -2.13 0.277 -0.1700 -3.24 0.095 -0.1700 Tabulated from data in file CL00755.DAT & reduced using program Q02.00L Average Reynolds #: 199400 Number of angles of attack: 49 alpha / Cl / Cm -2.92 0.052 -0.1700 -2.05 0.170 -0.1700 -1.15 0.329 -0.1700 -0.08 0.596 -0.1700 1.19 0.736 -0.1700 2.05 0.825 -0.1700 3.05 0.928 -0.1700 4.06 1.021 -0.1700 5.24 1.107 -0.1700 6.08 1.153 -0.1700 7.19 1.211 -0.1700 8.16 1.258 -0.1700 9.21 1.304 -0.1700 10.13 1.339 -0.1700 11.10 1.391 -0.1700 12.35 1.429 -0.1700 13.07 1.421 -0.1700 14.10 1.370 -0.1700 15.09 1.325 -0.1700 15.98 1.204 -0.1700 16.92 1.215 -0.1700 18.03 1.169 -0.1700 19.09 1.169 -0.1700 20.06 1.189 -0.1700 21.06 1.212 -0.1700 20.41 1.192 -0.1700 19.46 1.177 -0.1700 18.39 1.174 -0.1700 17.43 1.202 -0.1700 16.43 1.206 -0.1700 15.51 1.188 -0.1700 14.64 1.353 -0.1700 13.47 1.416 -0.1700 12.71 1.422 -0.1700 11.45 1.411 -0.1700 10.46 1.351 -0.1700 9.46 1.309 -0.1700 8.37 1.263 -0.1700 7.41 1.218 -0.1700 6.31 1.158 -0.1700 5.37 1.108 -0.1700 4.16 1.025 -0.1700 3.31 0.947 -0.1700 2.19 0.830 -0.1700 1.15 0.724 -0.1700 0.26 0.627 -0.1700 -0.87 0.499 -0.1700 -1.94 0.184 -0.1700 -2.98 0.044 -0.1700 Tabulated from data in file CL00871.DAT & reduced using program Q02.00L Average Reynolds #: 299200 Number of angles of attack: 49 alpha / Cl / Cm -2.79 0.073 -0.1700 -1.79 0.428 -0.1700 -0.59 0.572 -0.1700 0.43 0.685 -0.1700 1.45 0.792 -0.1700 2.42 0.893 -0.1700 3.65 1.015 -0.1700 4.57 1.081 -0.1700 5.52 1.139 -0.1700 6.57 1.201 -0.1700 7.76 1.262 -0.1700 8.70 1.304 -0.1700 9.76 1.360 -0.1700 10.72 1.432 -0.1700 11.76 1.478 -0.1700 12.81 1.452 -0.1700 13.00 1.421 -0.1700 14.19 1.341 -0.1700 15.31 1.255 -0.1700 16.13 1.169 -0.1700 17.38 1.187 -0.1700 18.29 1.174 -0.1700 19.20 1.155 -0.1700 20.16 1.168 -0.1700 21.22 1.201 -0.1700 20.00 1.180 -0.1700 18.99 1.168 -0.1700 18.35 1.171 -0.1700 17.16 1.179 -0.1700 15.95 1.226 -0.1700 15.16 1.340 -0.1700 14.11 1.385 -0.1700 12.85 1.429 -0.1700 12.67 1.439 -0.1700 10.72 1.429 -0.1700 9.74 1.353 -0.1700 8.84 1.305 -0.1700 7.92 1.262 -0.1700 6.90 1.212 -0.1700 5.77 1.148 -0.1700 4.70 1.084 -0.1700 3.69 1.012 -0.1700 2.74 0.922 -0.1700 1.89 0.832 -0.1700 0.77 0.713 -0.1700 -0.29 0.594 -0.1700 -1.10 0.504 -0.1700 -2.30 0.333 -0.1700 -2.28 0.162 -0.1700 Tabulated from data in file CL00873.DAT & reduced using program Q02.00L File davis3r.lft created on 09-12-1997 at 13:46:17 using program FORMAT