Airfoil: RG14 Builder: R. Cavazos Comment: clean Number of Reynolds #'s: 4 Average Reynolds #: 60400 Number of angles of attack: 49 alpha / Cl / Cm -6.16 -0.494 -0.0373 -4.64 -0.375 -0.0365 -3.86 -0.312 -0.0327 -2.71 -0.221 -0.0251 -1.94 -0.150 -0.0142 -0.82 -0.065 -0.0193 0.37 0.053 -0.0228 1.13 0.125 -0.0150 2.34 0.342 -0.0355 3.54 0.509 -0.0383 4.34 0.572 -0.0329 5.53 0.679 -0.0349 6.31 0.737 -0.0346 7.48 0.821 -0.0315 8.63 0.904 -0.0283 9.37 0.939 -0.0242 10.49 0.986 -0.0233 11.59 0.937 -0.0717 12.31 0.887 -0.1036 13.46 0.841 -0.1124 14.59 0.841 -0.1183 15.35 0.832 -0.1198 16.54 0.893 -0.1321 17.70 0.901 -0.1369 18.47 0.913 -0.1411 16.79 0.880 -0.1355 15.75 0.887 -0.1402 14.69 0.855 -0.1317 13.67 0.845 -0.1232 12.68 0.836 -0.1194 11.68 0.908 -0.1070 10.73 0.984 -0.0434 9.76 0.964 -0.0287 8.79 0.921 -0.0298 7.80 0.865 -0.0332 6.78 0.797 -0.0364 5.74 0.723 -0.0408 4.69 0.622 -0.0478 3.63 0.530 -0.0531 2.56 0.403 -0.0552 1.51 0.192 -0.0321 0.49 0.101 -0.0265 -0.51 -0.006 -0.0197 -1.50 -0.108 -0.0256 -2.49 -0.188 -0.0287 -3.50 -0.267 -0.0292 -4.48 -0.347 -0.0316 -5.53 -0.436 -0.0350 -6.57 -0.509 -0.0321 Tabulated from data in file AB01057.DAT & reduced using program Q06.01L Average Reynolds #: 100700 Number of angles of attack: 49 alpha / Cl / Cm -6.09 -0.431 -0.0369 -4.95 -0.336 -0.0345 -3.78 -0.245 -0.0311 -2.61 -0.145 -0.0294 -1.85 -0.096 -0.0196 -0.66 -0.005 -0.0218 0.10 0.061 -0.0215 1.31 0.218 -0.0395 2.53 0.407 -0.0489 3.34 0.498 -0.0483 4.58 0.613 -0.0426 5.39 0.682 -0.0399 6.62 0.801 -0.0382 7.39 0.862 -0.0355 8.56 0.945 -0.0313 9.34 0.993 -0.0284 10.46 1.040 -0.0239 11.55 1.005 -0.0738 12.65 0.922 -0.1150 13.41 0.905 -0.1228 14.61 0.946 -0.1355 15.38 0.920 -0.1320 16.59 0.920 -0.1337 17.40 0.937 -0.1384 18.61 0.949 -0.1373 16.82 0.913 -0.1395 15.72 0.928 -0.1414 14.63 0.927 -0.1384 13.88 0.929 -0.1364 12.83 0.928 -0.1290 11.82 0.988 -0.1037 10.84 1.042 -0.0290 9.88 1.020 -0.0274 8.88 0.965 -0.0302 7.86 0.904 -0.0339 6.81 0.823 -0.0368 5.76 0.725 -0.0385 4.69 0.625 -0.0417 3.62 0.524 -0.0480 2.52 0.410 -0.0529 1.45 0.256 -0.0462 0.71 0.137 -0.0318 -0.32 0.036 -0.0229 -1.36 -0.060 -0.0176 -2.38 -0.130 -0.0236 -3.40 -0.209 -0.0263 -4.42 -0.295 -0.0282 -5.47 -0.376 -0.0312 -6.54 -0.474 -0.0297 Tabulated from data in file AB01059.DAT & reduced using program Q06.01L Average Reynolds #: 201100 Number of angles of attack: 49 alpha / Cl / Cm -6.41 -0.492 -0.0309 -4.39 -0.322 -0.0309 -3.93 -0.282 -0.0302 -2.66 -0.170 -0.0298 -1.85 -0.097 -0.0298 -0.59 0.069 -0.0374 0.25 0.195 -0.0455 1.51 0.351 -0.0486 2.35 0.431 -0.0466 3.63 0.550 -0.0432 4.44 0.624 -0.0415 5.27 0.700 -0.0399 6.53 0.812 -0.0370 7.34 0.881 -0.0346 8.54 0.974 -0.0308 9.72 1.054 -0.0268 10.47 1.084 -0.0227 11.56 1.089 -0.0448 12.55 1.077 -0.1022 13.60 1.027 -0.1251 14.30 1.009 -0.1321 15.36 0.945 -0.1355 16.44 0.937 -0.1357 17.52 0.943 -0.1376 18.60 0.960 -0.1410 16.78 0.943 -0.1393 15.66 0.941 -0.1356 14.90 0.996 -0.1375 13.81 1.032 -0.1311 12.74 1.064 -0.1117 11.75 1.088 -0.0694 11.12 1.095 -0.0215 9.86 1.061 -0.0255 8.86 0.997 -0.0291 7.83 0.918 -0.0319 6.77 0.831 -0.0350 5.68 0.739 -0.0382 4.56 0.637 -0.0410 3.79 0.566 -0.0428 2.70 0.464 -0.0452 1.55 0.350 -0.0476 0.75 0.259 -0.0472 -0.72 0.049 -0.0360 -1.82 -0.091 -0.0285 -2.52 -0.157 -0.0272 -3.62 -0.257 -0.0265 -4.39 -0.323 -0.0277 -5.54 -0.410 -0.0316 -6.72 -0.517 -0.0261 Tabulated from data in file AB01061.DAT & reduced using program Q06.01L Average Reynolds #: 301900 Number of angles of attack: 49 alpha / Cl / Cm -6.17 -0.484 -0.0347 -4.69 -0.356 -0.0315 -3.91 -0.286 -0.0304 -2.74 -0.155 -0.0345 -1.64 -0.008 -0.0439 -0.86 0.083 -0.0455 0.29 0.219 -0.0461 1.46 0.346 -0.0455 2.37 0.434 -0.0441 3.65 0.562 -0.0419 4.53 0.646 -0.0410 5.39 0.727 -0.0399 6.65 0.840 -0.0376 7.47 0.912 -0.0362 8.67 1.009 -0.0331 9.43 1.063 -0.0305 10.56 1.117 -0.0249 11.64 1.131 -0.0217 12.38 1.133 -0.0817 13.50 1.123 -0.1102 14.57 1.108 -0.1267 15.49 1.053 -0.1340 16.46 0.994 -0.1389 17.44 0.983 -0.1379 18.30 1.010 -0.1426 16.79 0.995 -0.1399 15.83 1.005 -0.1384 14.90 1.063 -0.1340 13.67 1.146 -0.1146 12.74 1.153 -0.0916 11.74 1.142 -0.0224 10.57 1.126 -0.0229 9.95 1.098 -0.0252 8.67 1.016 -0.0301 7.68 0.936 -0.0328 6.65 0.847 -0.0350 5.91 0.779 -0.0364 4.79 0.677 -0.0387 3.63 0.573 -0.0403 2.79 0.485 -0.0419 1.58 0.351 -0.0451 0.28 0.216 -0.0463 -0.54 0.115 -0.0449 -1.73 -0.022 -0.0436 -2.52 -0.128 -0.0361 -3.69 -0.272 -0.0295 -4.53 -0.349 -0.0301 -5.78 -0.452 -0.0352 -6.63 -0.531 -0.0316 Tabulated from data in file AB01063.DAT & reduced using program Q06.01L File RG14.LFT created on 10-24-1997 at 19:34:41 using program FORMAT