Airfoil: S8037 Builder: T. Lampe Comment: clean Number of Reynolds #'s: 5 Average Reynolds #: 101100 Number of angles of attack: 57 alpha / Cl / Cm -6.42 -0.326 -0.0562 -4.88 -0.223 -0.0570 -3.95 -0.178 -0.0501 -2.74 -0.101 -0.0383 -1.83 -0.041 -0.0296 -0.39 0.127 -0.0330 0.28 0.236 -0.0415 1.21 0.392 -0.0544 2.42 0.499 -0.0570 3.35 0.560 -0.0502 4.31 0.643 -0.0458 5.79 0.780 -0.0425 6.47 0.838 -0.0410 7.39 0.918 -0.0388 8.82 1.039 -0.0346 9.46 1.092 -0.0333 10.86 1.184 -0.0274 11.50 1.212 -0.0238 12.38 1.237 -0.0171 13.54 1.250 -0.0106 14.43 1.252 -0.0075 15.83 1.252 -0.0057 16.46 1.246 -0.0075 17.71 0.812 -0.0866 18.35 0.796 -0.0829 19.28 0.819 -0.0876 20.48 0.886 -0.1030 21.36 0.887 -0.1046 22.84 0.943 -0.1168 20.82 0.872 -0.1127 19.80 0.839 -0.1031 18.76 0.812 -0.0963 17.70 0.771 -0.0902 16.55 0.747 -0.0826 15.75 0.752 -0.0800 14.72 0.795 -0.0811 13.74 0.909 -0.0747 12.78 1.243 -0.0244 11.78 1.229 -0.0288 10.76 1.186 -0.0341 9.76 1.123 -0.0377 8.74 1.039 -0.0395 7.71 0.951 -0.0424 6.95 0.884 -0.0443 5.64 0.769 -0.0469 4.84 0.697 -0.0486 3.83 0.607 -0.0525 2.81 0.533 -0.0578 1.79 0.470 -0.0641 0.77 0.327 -0.0536 -0.25 0.157 -0.0407 -1.57 -0.007 -0.0355 -2.28 -0.055 -0.0406 -3.56 -0.147 -0.0513 -4.31 -0.193 -0.0588 -5.66 -0.268 -0.0638 -6.47 -0.327 -0.0612 Tabulated from data in file CL01039.DAT & reduced using program Q06.01L Average Reynolds #: 201800 Number of angles of attack: 57 alpha / Cl / Cm -6.04 -0.320 -0.0494 -4.80 -0.226 -0.0474 -3.89 -0.166 -0.0436 -2.40 -0.044 -0.0378 -1.76 0.012 -0.0356 -0.87 0.090 -0.0330 0.31 0.204 -0.0308 1.20 0.302 -0.0315 2.39 0.474 -0.0418 3.60 0.638 -0.0521 4.26 0.693 -0.0502 5.46 0.796 -0.0466 6.36 0.878 -0.0444 7.52 0.979 -0.0406 8.39 1.050 -0.0378 9.51 1.134 -0.0331 10.35 1.186 -0.0289 11.45 1.245 -0.0224 12.51 1.270 -0.0139 13.55 1.273 -0.0114 14.61 1.271 -0.0093 15.79 1.273 -0.0080 16.58 1.272 -0.0075 17.76 1.289 -0.0127 18.55 1.290 -0.0170 19.69 1.267 -0.0229 20.46 1.253 -0.0293 21.48 1.246 -0.0402 22.27 0.899 -0.1100 20.40 0.861 -0.1038 19.79 0.861 -0.1051 18.46 0.828 -0.0968 17.89 0.808 -0.0907 16.70 0.807 -0.0851 15.86 0.823 -0.0827 14.73 0.875 -0.0770 13.75 1.278 -0.0130 12.84 1.279 -0.0142 11.99 1.270 -0.0197 10.81 1.216 -0.0272 9.91 1.160 -0.0319 8.99 1.095 -0.0359 7.73 0.994 -0.0406 6.66 0.900 -0.0437 5.88 0.832 -0.0456 4.82 0.739 -0.0485 3.73 0.651 -0.0522 2.51 0.493 -0.0439 1.72 0.369 -0.0339 0.67 0.242 -0.0303 -0.37 0.134 -0.0304 -1.38 0.041 -0.0328 -2.42 -0.046 -0.0360 -3.49 -0.134 -0.0395 -4.56 -0.207 -0.0441 -5.42 -0.268 -0.0478 -6.60 -0.355 -0.0504 Tabulated from data in file CL01041.DAT & reduced using program Q06.01L Average Reynolds #: 302500 Number of angles of attack: 57 alpha / Cl / Cm -6.05 -0.338 -0.0450 -4.79 -0.231 -0.0437 -3.85 -0.157 -0.0411 -2.85 -0.079 -0.0370 -1.79 0.014 -0.0346 -0.70 0.121 -0.0336 0.43 0.236 -0.0324 1.22 0.315 -0.0311 2.29 0.438 -0.0325 3.34 0.586 -0.0414 4.43 0.734 -0.0496 5.56 0.835 -0.0472 6.32 0.899 -0.0447 7.40 0.985 -0.0405 8.45 1.062 -0.0356 9.47 1.133 -0.0303 10.45 1.194 -0.0250 11.42 1.243 -0.0192 12.77 1.266 -0.0114 13.78 1.279 -0.0135 14.42 1.284 -0.0132 15.81 1.280 -0.0102 16.46 1.284 -0.0121 17.85 1.295 -0.0138 18.47 1.298 -0.0175 19.88 1.289 -0.0267 20.53 1.278 -0.0315 22.07 1.298 -0.0474 22.45 1.288 -0.0507 20.92 1.278 -0.0362 19.90 1.286 -0.0286 18.88 1.299 -0.0215 17.90 1.301 -0.0165 16.94 1.301 -0.0136 15.98 1.292 -0.0133 15.01 1.290 -0.0144 14.03 1.283 -0.0150 13.08 1.273 -0.0133 11.89 1.257 -0.0159 11.08 1.226 -0.0212 10.01 1.163 -0.0271 8.89 1.089 -0.0328 7.95 1.022 -0.0374 6.93 0.944 -0.0419 5.85 0.855 -0.0460 4.70 0.758 -0.0496 3.82 0.653 -0.0467 2.67 0.485 -0.0367 1.43 0.336 -0.0326 0.54 0.243 -0.0339 -0.38 0.149 -0.0348 -1.31 0.056 -0.0353 -2.58 -0.058 -0.0376 -3.56 -0.138 -0.0406 -4.52 -0.208 -0.0438 -5.47 -0.290 -0.0454 -6.42 -0.369 -0.0473 Tabulated from data in file CL01043.DAT & reduced using program Q06.01L Average Reynolds #: 403400 Number of angles of attack: 57 alpha / Cl / Cm -5.98 -0.340 -0.0437 -4.88 -0.241 -0.0433 -3.84 -0.151 -0.0411 -2.63 -0.057 -0.0364 -1.71 0.025 -0.0347 -0.76 0.121 -0.0340 0.24 0.228 -0.0338 1.26 0.334 -0.0332 2.36 0.452 -0.0334 3.46 0.587 -0.0377 4.56 0.734 -0.0456 5.63 0.849 -0.0479 6.40 0.909 -0.0449 7.55 0.994 -0.0390 8.64 1.072 -0.0336 9.38 1.122 -0.0298 10.88 1.206 -0.0211 11.53 1.231 -0.0164 12.78 1.262 -0.0141 13.71 1.273 -0.0151 14.58 1.281 -0.0153 15.88 1.279 -0.0143 16.49 1.282 -0.0162 17.82 1.275 -0.0199 18.46 1.279 -0.0218 19.65 1.263 -0.0267 20.53 1.252 -0.0328 21.73 1.291 -0.0455 22.40 1.308 -0.0563 21.01 1.279 -0.0377 19.95 1.284 -0.0291 19.01 1.290 -0.0231 17.92 1.284 -0.0194 16.97 1.289 -0.0162 15.98 1.293 -0.0150 14.94 1.288 -0.0157 13.97 1.275 -0.0155 12.96 1.264 -0.0132 12.00 1.240 -0.0111 11.06 1.212 -0.0161 10.03 1.158 -0.0227 8.88 1.083 -0.0294 7.84 1.010 -0.0347 6.61 0.919 -0.0409 5.64 0.846 -0.0452 4.62 0.735 -0.0435 3.64 0.603 -0.0373 2.66 0.478 -0.0330 1.60 0.363 -0.0326 0.44 0.242 -0.0337 -0.35 0.160 -0.0342 -1.38 0.052 -0.0347 -2.42 -0.044 -0.0358 -3.44 -0.125 -0.0391 -4.39 -0.204 -0.0414 -5.63 -0.311 -0.0436 -6.50 -0.385 -0.0446 Tabulated from data in file CL01045.DAT & reduced using program Q06.01L Average Reynolds #: 504500 Number of angles of attack: 53 alpha / Cl / Cm -7.31 -0.479 -0.0468 -4.69 -0.261 -0.0421 -3.76 -0.180 -0.0406 -2.83 -0.104 -0.0381 -1.79 -0.015 -0.0354 -0.72 0.094 -0.0345 0.43 0.219 -0.0344 1.60 0.345 -0.0341 2.32 0.422 -0.0340 3.63 0.565 -0.0350 4.89 0.724 -0.0402 5.62 0.818 -0.0446 7.05 0.942 -0.0410 7.90 1.002 -0.0364 8.72 1.061 -0.0323 10.05 1.149 -0.0250 10.79 1.191 -0.0211 11.98 1.231 -0.0145 12.57 1.242 -0.0127 13.60 1.264 -0.0138 14.66 1.278 -0.0145 15.73 1.286 -0.0149 16.80 1.296 -0.0159 17.80 1.295 -0.0178 18.83 1.304 -0.0236 19.80 1.308 -0.0322 20.88 1.319 -0.0407 18.61 1.310 -0.0260 17.85 1.301 -0.0195 16.66 1.294 -0.0168 15.84 1.295 -0.0162 14.66 1.281 -0.0148 13.87 1.271 -0.0143 12.69 1.246 -0.0112 11.91 1.231 -0.0124 10.57 1.178 -0.0199 9.61 1.119 -0.0244 8.53 1.044 -0.0297 7.86 0.996 -0.0338 6.64 0.908 -0.0407 5.26 0.767 -0.0410 4.51 0.669 -0.0367 3.74 0.572 -0.0336 2.19 0.403 -0.0334 1.41 0.320 -0.0339 0.65 0.238 -0.0344 -0.70 0.094 -0.0344 -1.88 -0.026 -0.0352 -2.53 -0.083 -0.0370 -3.72 -0.183 -0.0403 -4.81 -0.278 -0.0423 -5.87 -0.371 -0.0439 -6.48 -0.422 -0.0450 Tabulated from data in file CL01788.DAT & reduced using program Q06.01L File S8037.LFT created on 10-24-1997 at 19:34:41 using program FORMAT