Airfoil: M06-13-128 (B) Builder: M. Allen Comment: clean Number of Reynolds #'s: 6 Average Reynolds #: 61400 Number of angles of attack: 57 alpha / Cl / Cm -6.01 -0.189 0.0040 -5.19 -0.103 0.0040 -4.16 -0.003 0.0040 -3.18 0.062 0.0040 -2.13 0.109 0.0040 -1.15 0.154 0.0040 -0.13 0.206 0.0040 0.91 0.240 0.0040 1.89 0.287 0.0040 2.92 0.349 0.0040 3.90 0.390 0.0040 4.92 0.433 0.0040 5.94 0.464 0.0040 6.97 0.471 0.0040 7.96 0.511 0.0040 8.95 0.528 0.0040 10.01 0.565 0.0040 10.98 0.612 0.0040 12.00 0.628 0.0040 13.03 0.664 0.0040 14.00 0.686 0.0040 15.00 0.723 0.0040 16.04 0.773 0.0040 17.01 0.820 0.0040 18.03 0.899 0.0040 19.08 1.037 0.0040 20.21 1.301 0.0040 21.14 1.197 0.0040 22.16 1.205 0.0040 21.66 1.130 0.0040 20.66 1.182 0.0040 19.61 1.206 0.0040 18.69 1.222 0.0040 17.69 1.280 0.0040 16.69 1.346 0.0040 15.71 1.387 0.0040 14.55 0.689 0.0040 13.51 0.657 0.0040 12.51 0.621 0.0040 11.49 0.586 0.0040 10.48 0.554 0.0040 9.51 0.518 0.0040 8.48 0.491 0.0040 7.46 0.456 0.0040 6.55 0.460 0.0040 5.49 0.423 0.0040 4.49 0.391 0.0040 3.44 0.328 0.0040 2.46 0.285 0.0040 1.42 0.235 0.0040 0.41 0.184 0.0040 -0.59 0.145 0.0040 -1.60 0.097 0.0040 -2.60 0.043 0.0040 -3.65 -0.014 0.0040 -4.62 -0.099 0.0040 -5.68 -0.199 0.0040 Tabulated from data in file JG00192.DAT & reduced using program Q01.00L Average Reynolds #: 71600 Number of angles of attack: 57 alpha / Cl / Cm -5.95 -0.196 0.0040 -4.86 -0.083 0.0040 -3.85 0.002 0.0040 -2.76 0.064 0.0040 -1.85 0.111 0.0040 -0.70 0.162 0.0040 0.22 0.216 0.0040 1.33 0.259 0.0040 2.35 0.313 0.0040 3.20 0.360 0.0040 4.33 0.414 0.0040 5.18 0.447 0.0040 6.34 0.509 0.0040 7.30 0.544 0.0040 8.28 0.562 0.0040 9.24 0.550 0.0040 10.39 0.596 0.0040 11.33 0.632 0.0040 12.30 0.661 0.0040 13.46 0.710 0.0040 14.38 0.724 0.0040 15.32 0.780 0.0040 16.33 0.823 0.0040 17.31 0.878 0.0040 18.44 1.287 0.0040 19.42 1.229 0.0040 20.54 1.221 0.0040 21.36 1.152 0.0040 22.44 1.153 0.0040 21.33 1.176 0.0040 20.34 1.224 0.0040 19.42 1.229 0.0040 18.37 1.269 0.0040 17.41 1.324 0.0040 16.40 1.400 0.0040 15.40 1.451 0.0040 14.41 1.499 0.0040 13.22 0.648 0.0040 12.23 0.623 0.0040 11.18 0.603 0.0040 10.21 0.576 0.0040 9.23 0.528 0.0040 8.20 0.490 0.0040 7.21 0.471 0.0040 6.13 0.462 0.0040 5.14 0.421 0.0040 4.13 0.381 0.0040 3.07 0.331 0.0040 2.06 0.268 0.0040 1.01 0.215 0.0040 0.03 0.167 0.0040 -0.90 0.128 0.0040 -1.97 0.063 0.0040 -2.98 0.010 0.0040 -3.97 -0.047 0.0040 -4.97 -0.139 0.0040 -6.12 -0.257 0.0040 Tabulated from data in file JG00193.DAT & reduced using program Q01.00L Average Reynolds #: 102000 Number of angles of attack: 57 alpha / Cl / Cm -6.04 -0.275 0.0040 -4.92 -0.143 0.0040 -3.84 -0.030 0.0040 -2.73 0.055 0.0040 -1.77 0.116 0.0040 -0.73 0.161 0.0040 0.23 0.220 0.0040 1.19 0.254 0.0040 2.39 0.322 0.0040 3.31 0.367 0.0040 4.22 0.412 0.0040 5.43 0.464 0.0040 6.39 0.511 0.0040 7.39 0.561 0.0040 8.34 0.624 0.0040 9.31 0.666 0.0040 10.34 0.727 0.0040 11.31 0.786 0.0040 12.36 0.829 0.0040 13.36 0.849 0.0040 14.36 0.850 0.0040 15.52 0.837 0.0040 16.55 0.860 0.0040 17.62 1.175 0.0040 18.59 1.218 0.0040 19.60 1.209 0.0040 20.46 1.204 0.0040 21.53 1.206 0.0040 22.46 1.099 0.0040 21.27 1.217 0.0040 20.39 1.217 0.0040 19.32 1.234 0.0040 18.36 1.237 0.0040 17.31 1.294 0.0040 16.39 1.388 0.0040 15.38 1.434 0.0040 14.46 1.492 0.0040 13.43 1.510 0.0040 12.43 1.435 0.0040 11.25 0.782 0.0040 10.22 0.732 0.0040 9.24 0.660 0.0040 8.20 0.595 0.0040 7.14 0.542 0.0040 6.08 0.479 0.0040 5.13 0.436 0.0040 4.10 0.383 0.0040 3.12 0.341 0.0040 2.01 0.281 0.0040 1.00 0.222 0.0040 0.04 0.186 0.0040 -0.99 0.131 0.0040 -2.04 0.072 0.0040 -3.04 0.001 0.0040 -4.01 -0.071 0.0040 -5.09 -0.187 0.0040 -6.03 -0.288 0.0040 Tabulated from data in file JG00194.DAT & reduced using program Q01.00L Average Reynolds #: 152700 Number of angles of attack: 57 alpha / Cl / Cm -6.03 -0.308 0.0040 -4.73 -0.151 0.0040 -3.76 -0.034 0.0040 -2.63 0.065 0.0040 -1.71 0.134 0.0040 -0.79 0.185 0.0040 0.44 0.242 0.0040 1.26 0.292 0.0040 2.43 0.356 0.0040 3.23 0.393 0.0040 4.46 0.466 0.0040 5.33 0.502 0.0040 6.54 0.566 0.0040 7.30 0.603 0.0040 8.43 0.657 0.0040 9.40 0.703 0.0040 10.34 0.739 0.0040 11.36 0.780 0.0040 12.34 0.808 0.0040 13.58 0.888 0.0040 14.53 0.992 0.0040 15.48 1.319 0.0040 16.52 1.327 0.0040 17.53 1.255 0.0040 18.53 1.238 0.0040 19.59 1.218 0.0040 20.60 1.220 0.0040 21.44 1.232 0.0040 22.53 1.087 0.0040 21.15 1.219 0.0040 20.34 1.241 0.0040 19.36 1.231 0.0040 18.29 1.235 0.0040 17.30 1.275 0.0040 16.31 1.343 0.0040 15.39 1.428 0.0040 14.39 1.479 0.0040 13.41 1.511 0.0040 12.44 1.500 0.0040 11.46 1.411 0.0040 10.37 1.270 0.0040 9.23 0.682 0.0040 8.09 0.631 0.0040 7.13 0.589 0.0040 6.04 0.531 0.0040 5.03 0.472 0.0040 4.03 0.428 0.0040 3.04 0.374 0.0040 1.91 0.316 0.0040 1.03 0.267 0.0040 0.05 0.209 0.0040 -1.02 0.157 0.0040 -2.13 0.090 0.0040 -3.01 0.018 0.0040 -4.00 -0.076 0.0040 -5.13 -0.209 0.0040 -6.04 -0.312 0.0040 Tabulated from data in file JG00195.DAT & reduced using program Q01.00L Average Reynolds #: 203200 Number of angles of attack: 57 alpha / Cl / Cm -6.05 -0.329 0.0040 -4.64 -0.159 0.0040 -3.63 -0.041 0.0040 -2.67 0.057 0.0040 -1.58 0.151 0.0040 -0.50 0.218 0.0040 0.25 0.262 0.0040 1.37 0.328 0.0040 2.39 0.385 0.0040 3.46 0.460 0.0040 4.45 0.531 0.0040 5.53 0.624 0.0040 6.34 0.774 0.0040 7.55 0.967 0.0040 8.55 1.101 0.0040 9.59 1.227 0.0040 10.43 1.322 0.0040 11.46 1.427 0.0040 12.44 1.491 0.0040 13.41 1.479 0.0040 14.39 1.420 0.0040 15.56 1.338 0.0040 16.52 1.291 0.0040 17.62 1.228 0.0040 18.42 1.212 0.0040 19.52 1.214 0.0040 20.45 1.214 0.0040 21.46 1.203 0.0040 22.36 1.151 0.0040 21.19 1.208 0.0040 20.20 1.213 0.0040 19.16 1.209 0.0040 18.24 1.215 0.0040 17.24 1.253 0.0040 16.32 1.304 0.0040 15.32 1.352 0.0040 14.33 1.419 0.0040 13.36 1.477 0.0040 12.40 1.484 0.0040 11.37 1.418 0.0040 10.34 1.310 0.0040 9.32 1.190 0.0040 8.32 1.067 0.0040 7.20 0.894 0.0040 5.99 0.719 0.0040 4.87 0.571 0.0040 3.93 0.479 0.0040 2.95 0.419 0.0040 1.86 0.348 0.0040 0.96 0.296 0.0040 -0.09 0.238 0.0040 -1.16 0.171 0.0040 -2.02 0.107 0.0040 -3.20 -0.007 0.0040 -4.10 -0.107 0.0040 -5.19 -0.238 0.0040 -6.14 -0.345 0.0040 Tabulated from data in file JG00196.DAT & reduced using program Q01.00L Average Reynolds #: 304200 Number of angles of attack: 57 alpha / Cl / Cm -6.03 -0.363 0.0040 -4.68 -0.203 0.0040 -3.83 -0.101 0.0040 -2.55 0.041 0.0040 -1.67 0.133 0.0040 -0.80 0.223 0.0040 0.42 0.350 0.0040 1.56 0.462 0.0040 2.43 0.545 0.0040 3.56 0.662 0.0040 4.41 0.751 0.0040 5.50 0.863 0.0040 6.46 0.963 0.0040 7.39 1.061 0.0040 8.43 1.171 0.0040 9.41 1.276 0.0040 10.48 1.388 0.0040 11.59 1.480 0.0040 12.49 1.511 0.0040 13.55 1.469 0.0040 14.53 1.399 0.0040 15.59 1.345 0.0040 16.50 1.299 0.0040 17.51 1.257 0.0040 18.62 1.241 0.0040 19.57 1.237 0.0040 20.72 1.233 0.0040 21.68 1.222 0.0040 22.52 1.230 0.0040 21.03 1.240 0.0040 20.09 1.244 0.0040 19.29 1.241 0.0040 18.15 1.244 0.0040 17.19 1.256 0.0040 16.32 1.308 0.0040 15.37 1.355 0.0040 14.32 1.410 0.0040 13.42 1.471 0.0040 12.39 1.509 0.0040 11.38 1.465 0.0040 10.39 1.379 0.0040 9.31 1.262 0.0040 8.28 1.151 0.0040 7.29 1.044 0.0040 6.21 0.932 0.0040 5.19 0.825 0.0040 4.13 0.712 0.0040 3.07 0.602 0.0040 1.86 0.477 0.0040 0.82 0.380 0.0040 -0.02 0.286 0.0040 -1.24 0.166 0.0040 -2.22 0.064 0.0040 -3.20 -0.042 0.0040 -4.11 -0.147 0.0040 -5.16 -0.279 0.0040 -6.13 -0.382 0.0040 Tabulated from data in file JG00198.DAT & reduced using program Q01.00L File m06b.lft created on 12-05-1997 at 15:25:50 using program FORMAT