Airfoil: S8036 Builder: T. Lampe Comment: clean Number of Reynolds #'s: 5 Average Reynolds #: 101200 Number of angles of attack: 49 alpha / Cl / Cm -5.59 -0.384 -0.0337 -4.53 -0.252 -0.0383 -3.47 -0.154 -0.0335 -2.19 -0.059 -0.0264 -1.28 0.009 -0.0213 -0.58 0.077 -0.0212 0.44 0.190 -0.0248 1.51 0.346 -0.0369 2.61 0.500 -0.0490 3.72 0.571 -0.0457 5.09 0.678 -0.0383 5.48 0.714 -0.0372 6.57 0.817 -0.0336 7.65 0.908 -0.0302 8.71 0.990 -0.0272 9.73 1.060 -0.0234 10.75 1.100 -0.0165 11.79 1.129 -0.0099 12.80 1.154 -0.0057 13.82 1.166 -0.0029 14.68 0.717 -0.0755 15.76 0.720 -0.0785 16.81 0.720 -0.0828 17.53 0.714 -0.0825 18.61 0.768 -0.0925 16.64 0.727 -0.0895 16.01 0.730 -0.0894 15.06 0.733 -0.0845 13.72 0.788 -0.0784 13.22 1.165 -0.0133 12.09 1.142 -0.0130 11.20 1.116 -0.0173 10.03 1.079 -0.0250 9.16 1.030 -0.0296 7.97 0.941 -0.0327 7.04 0.865 -0.0359 6.09 0.780 -0.0388 5.11 0.690 -0.0430 3.65 0.573 -0.0488 3.00 0.534 -0.0521 1.96 0.416 -0.0453 0.92 0.253 -0.0323 -0.06 0.127 -0.0259 -1.27 0.016 -0.0246 -2.20 -0.057 -0.0290 -3.13 -0.125 -0.0348 -4.34 -0.229 -0.0406 -5.32 -0.339 -0.0382 -6.32 -0.459 -0.0284 Tabulated from data in file CL01028.DAT & reduced using program Q06.01L Average Reynolds #: 201900 Number of angles of attack: 49 alpha / Cl / Cm -5.57 -0.333 -0.0394 -4.59 -0.260 -0.0358 -3.61 -0.174 -0.0333 -2.60 -0.084 -0.0306 -1.62 0.001 -0.0286 -0.64 0.089 -0.0269 0.44 0.188 -0.0259 1.43 0.291 -0.0241 2.41 0.393 -0.0239 3.74 0.608 -0.0361 4.88 0.741 -0.0407 5.57 0.797 -0.0388 6.55 0.875 -0.0353 8.00 0.980 -0.0284 8.61 1.023 -0.0257 9.99 1.114 -0.0194 10.58 1.139 -0.0156 11.80 1.178 -0.0085 12.66 1.192 -0.0065 13.82 1.212 -0.0046 14.69 1.226 -0.0044 15.96 1.242 -0.0050 16.95 1.251 -0.0083 17.95 1.258 -0.0137 18.55 0.824 -0.0989 16.99 0.779 -0.0929 15.54 0.744 -0.0849 15.11 0.774 -0.0858 14.15 1.218 -0.0059 13.12 1.203 -0.0078 12.12 1.187 -0.0082 11.10 1.160 -0.0132 10.05 1.117 -0.0197 9.21 1.065 -0.0234 8.16 0.993 -0.0279 7.06 0.916 -0.0332 5.83 0.819 -0.0379 4.83 0.738 -0.0413 3.82 0.628 -0.0383 2.77 0.442 -0.0247 1.88 0.337 -0.0223 0.97 0.244 -0.0230 -0.19 0.127 -0.0252 -1.18 0.032 -0.0252 -2.48 -0.082 -0.0282 -3.13 -0.132 -0.0299 -4.30 -0.234 -0.0326 -5.29 -0.306 -0.0369 -6.29 -0.385 -0.0397 Tabulated from data in file CL01030.DAT & reduced using program Q06.01L Average Reynolds #: 302600 Number of angles of attack: 53 alpha / Cl / Cm -5.75 -0.364 -0.0367 -4.81 -0.288 -0.0346 -3.54 -0.177 -0.0316 -2.53 -0.085 -0.0301 -1.41 0.021 -0.0285 -0.58 0.096 -0.0285 0.47 0.209 -0.0288 1.63 0.360 -0.0280 2.66 0.472 -0.0278 3.70 0.587 -0.0288 4.66 0.724 -0.0372 5.67 0.829 -0.0390 6.72 0.904 -0.0337 7.70 0.966 -0.0283 8.64 1.033 -0.0244 9.55 1.098 -0.0207 10.72 1.159 -0.0142 11.93 1.199 -0.0085 12.76 1.216 -0.0071 13.84 1.239 -0.0068 14.64 1.250 -0.0074 15.77 1.273 -0.0086 16.61 1.291 -0.0109 17.74 1.270 -0.0161 18.86 1.260 -0.0259 19.73 1.248 -0.0353 20.61 0.922 -0.1133 18.93 0.871 -0.1021 18.04 0.869 -0.0977 16.64 0.866 -0.0933 15.55 0.943 -0.0881 14.94 0.950 -0.0787 14.38 1.247 -0.0082 13.15 1.222 -0.0062 12.09 1.204 -0.0072 11.22 1.181 -0.0105 10.13 1.132 -0.0160 9.19 1.074 -0.0205 7.98 0.986 -0.0256 6.95 0.915 -0.0306 6.11 0.851 -0.0338 4.97 0.746 -0.0352 3.76 0.596 -0.0293 2.84 0.488 -0.0275 1.92 0.399 -0.0282 0.59 0.254 -0.0287 -0.22 0.135 -0.0288 -1.27 0.032 -0.0285 -2.32 -0.065 -0.0297 -3.43 -0.170 -0.0307 -4.79 -0.289 -0.0340 -5.19 -0.321 -0.0350 -6.81 -0.455 -0.0385 Tabulated from data in file CL01032.DAT & reduced using program Q06.01L Average Reynolds #: 403600 Number of angles of attack: 57 alpha / Cl / Cm -5.92 -0.392 -0.0354 -4.84 -0.297 -0.0348 -3.56 -0.181 -0.0316 -2.79 -0.111 -0.0301 -1.66 -0.002 -0.0296 -0.66 0.089 -0.0292 0.88 0.292 -0.0298 1.57 0.369 -0.0302 2.58 0.478 -0.0302 3.64 0.589 -0.0302 4.68 0.720 -0.0328 5.72 0.833 -0.0364 6.76 0.911 -0.0312 7.77 0.977 -0.0260 8.70 1.048 -0.0225 9.60 1.110 -0.0184 10.75 1.169 -0.0123 11.77 1.204 -0.0087 12.74 1.229 -0.0087 13.72 1.246 -0.0096 14.74 1.267 -0.0096 15.77 1.280 -0.0121 16.80 1.280 -0.0192 17.92 1.273 -0.0266 18.76 1.267 -0.0353 20.09 1.265 -0.0507 20.63 1.251 -0.0631 21.55 1.231 -0.0929 22.48 1.119 -0.1018 20.90 1.245 -0.0715 20.19 1.258 -0.0535 19.07 1.265 -0.0394 18.05 1.265 -0.0292 17.09 1.273 -0.0230 16.18 1.272 -0.0139 15.18 1.270 -0.0119 14.25 1.258 -0.0107 13.23 1.241 -0.0091 12.22 1.218 -0.0074 11.23 1.187 -0.0080 10.22 1.143 -0.0127 9.13 1.078 -0.0179 8.08 1.001 -0.0226 7.10 0.931 -0.0270 6.04 0.864 -0.0332 4.94 0.746 -0.0324 3.77 0.605 -0.0286 2.86 0.510 -0.0287 1.95 0.412 -0.0293 0.69 0.274 -0.0294 -0.37 0.155 -0.0295 -1.77 -0.007 -0.0294 -2.17 -0.045 -0.0296 -3.67 -0.194 -0.0315 -4.31 -0.249 -0.0328 -5.23 -0.328 -0.0342 -6.41 -0.437 -0.0355 Tabulated from data in file CL01036.DAT & reduced using program Q06.01L Average Reynolds #: 504800 Number of angles of attack: 53 alpha / Cl / Cm -6.67 -0.490 -0.0364 -4.34 -0.279 -0.0335 -3.32 -0.191 -0.0314 -2.70 -0.136 -0.0300 -1.57 -0.023 -0.0297 -0.50 0.098 -0.0297 0.69 0.231 -0.0303 1.89 0.366 -0.0311 2.59 0.442 -0.0311 4.03 0.591 -0.0311 4.84 0.677 -0.0311 5.68 0.773 -0.0327 7.23 0.904 -0.0290 8.05 0.967 -0.0259 8.81 1.025 -0.0229 10.07 1.110 -0.0170 10.76 1.145 -0.0133 11.93 1.186 -0.0086 13.01 1.216 -0.0092 14.07 1.239 -0.0109 15.12 1.251 -0.0136 15.68 1.261 -0.0159 17.14 1.279 -0.0350 17.71 1.289 -0.0397 19.07 1.269 -0.0413 20.04 1.267 -0.0567 20.68 1.260 -0.0710 18.77 1.271 -0.0389 17.88 1.267 -0.0297 16.90 1.276 -0.0326 16.11 1.263 -0.0196 14.90 1.253 -0.0142 14.05 1.241 -0.0125 12.89 1.215 -0.0100 12.06 1.192 -0.0080 10.78 1.147 -0.0116 9.79 1.095 -0.0170 8.70 1.017 -0.0220 7.61 0.931 -0.0264 6.91 0.880 -0.0297 5.66 0.767 -0.0314 4.98 0.691 -0.0302 3.60 0.545 -0.0306 2.76 0.457 -0.0309 1.26 0.296 -0.0309 0.47 0.208 -0.0304 -0.32 0.119 -0.0300 -1.56 -0.021 -0.0300 -2.78 -0.146 -0.0307 -3.47 -0.208 -0.0321 -4.72 -0.317 -0.0342 -5.33 -0.373 -0.0347 -6.57 -0.482 -0.0360 Tabulated from data in file CL01770.DAT & reduced using program Q06.01L File S8036.LFT created on 10-24-1997 at 19:34:41 using program FORMAT