Airfoil: ESA Builder: B. Halkett Comment: clean Number of Reynolds #'s: 4 Average Reynolds #: 101000 Number of angles of attack: 49 alpha / Cl / Cm -5.55 -0.546 0.0243 -4.20 -0.422 0.0227 -3.48 -0.346 0.0200 -2.16 -0.218 0.0205 -1.12 -0.083 0.0207 -0.10 0.010 0.0205 0.92 0.091 0.0259 1.94 0.171 0.0303 2.99 0.259 0.0317 3.72 0.323 0.0321 4.84 0.424 0.0314 5.93 0.537 0.0303 6.95 0.648 0.0290 7.97 0.741 0.0272 8.98 0.831 0.0252 9.96 0.909 0.0216 10.82 0.682 -0.0586 12.12 0.697 -0.0673 12.82 0.717 -0.0715 14.17 0.717 -0.0721 14.88 0.710 -0.0704 15.92 0.740 -0.0773 16.96 0.765 -0.0811 18.02 0.801 -0.0892 19.05 0.776 -0.0837 17.17 0.776 -0.0927 16.23 0.777 -0.0921 15.31 0.731 -0.0831 14.41 0.713 -0.0814 13.19 0.715 -0.0803 12.33 0.687 -0.0723 11.17 0.687 -0.0688 10.32 0.692 -0.0636 9.22 0.828 0.0148 8.43 0.777 0.0239 7.26 0.673 0.0269 6.40 0.589 0.0277 5.20 0.458 0.0308 4.33 0.369 0.0317 3.14 0.263 0.0341 2.28 0.195 0.0326 1.02 0.101 0.0292 0.19 0.037 0.0224 -0.97 -0.064 0.0205 -1.82 -0.197 0.0236 -2.96 -0.291 0.0178 -4.11 -0.415 0.0237 -4.95 -0.490 0.0246 -6.15 -0.599 0.0270 Tabulated from data in file AB01090.DAT & reduced using program Q06.01L Average Reynolds #: 201800 Number of angles of attack: 49 alpha / Cl / Cm -5.61 -0.582 0.0271 -4.24 -0.454 0.0293 -3.25 -0.367 0.0326 -2.24 -0.271 0.0347 -1.23 -0.189 0.0402 -0.21 -0.084 0.0437 0.74 0.049 0.0343 1.82 0.138 0.0355 2.79 0.233 0.0359 3.78 0.335 0.0358 4.77 0.440 0.0352 5.95 0.578 0.0335 6.88 0.671 0.0322 8.10 0.793 0.0303 9.02 0.887 0.0289 9.93 0.976 0.0275 11.12 1.090 0.0257 12.02 1.168 0.0241 13.22 1.230 0.0227 14.15 1.248 0.0159 14.59 0.747 -0.0841 16.04 0.763 -0.0865 17.10 0.788 -0.0905 18.20 0.799 -0.0912 18.94 0.830 -0.0957 17.28 0.776 -0.0909 16.25 0.757 -0.0886 15.25 0.737 -0.0850 14.23 0.741 -0.0857 13.22 0.735 -0.0851 12.24 0.725 -0.0824 11.27 0.729 -0.0788 10.35 0.775 -0.0693 9.72 0.957 0.0258 8.40 0.822 0.0289 7.35 0.715 0.0304 6.27 0.603 0.0321 5.37 0.493 0.0341 4.29 0.382 0.0356 3.21 0.270 0.0366 2.15 0.165 0.0369 1.06 0.069 0.0369 0.20 -0.004 0.0364 -0.85 -0.157 0.0446 -1.93 -0.236 0.0370 -3.02 -0.347 0.0352 -3.83 -0.423 0.0324 -5.01 -0.529 0.0278 -6.20 -0.648 0.0293 Tabulated from data in file AB01092.DAT & reduced using program Q06.01L Average Reynolds #: 302300 Number of angles of attack: 47 alpha / Cl / Cm -4.21 -0.487 0.0345 -3.20 -0.387 0.0369 -2.23 -0.285 0.0380 -1.27 -0.183 0.0385 -0.28 -0.107 0.0451 0.62 0.011 0.0409 1.92 0.142 0.0386 2.80 0.231 0.0386 3.81 0.354 0.0378 4.96 0.477 0.0365 5.83 0.570 0.0352 6.96 0.691 0.0333 8.03 0.805 0.0311 9.09 0.916 0.0291 9.87 0.999 0.0273 10.94 1.107 0.0249 11.99 1.203 0.0227 13.02 1.280 0.0212 14.03 1.317 0.0146 14.95 1.328 -0.0078 16.00 1.315 -0.0230 16.63 0.803 -0.0917 17.98 0.820 -0.0943 18.78 0.851 -0.0988 17.27 0.832 -0.0968 16.35 0.817 -0.0930 15.40 0.826 -0.0935 14.17 0.831 -0.0938 13.26 0.845 -0.0915 12.36 0.854 -0.0821 12.19 1.218 0.0208 10.55 1.063 0.0255 9.58 0.961 0.0283 8.37 0.838 0.0301 7.33 0.730 0.0317 6.43 0.636 0.0330 5.30 0.513 0.0349 4.40 0.419 0.0361 3.29 0.302 0.0373 2.15 0.168 0.0381 1.24 0.072 0.0381 0.27 -0.045 0.0450 -0.82 -0.157 0.0416 -2.01 -0.267 0.0391 -3.00 -0.372 0.0382 -4.01 -0.470 0.0361 -5.09 -0.572 0.0305 Tabulated from data in file AB01094.DAT & reduced using program Q06.01L Average Reynolds #: 402700 Number of angles of attack: 48 alpha / Cl / Cm -5.18 -0.608 0.0309 -3.85 -0.475 0.0363 -3.09 -0.393 0.0378 -1.88 -0.266 0.0389 -1.16 -0.187 0.0386 0.08 -0.083 0.0448 0.72 -0.022 0.0452 1.93 0.116 0.0416 2.87 0.253 0.0390 3.95 0.367 0.0379 5.00 0.477 0.0362 6.07 0.605 0.0344 7.12 0.726 0.0326 8.14 0.835 0.0303 9.14 0.942 0.0281 10.15 1.047 0.0263 11.11 1.145 0.0241 12.10 1.235 0.0220 13.48 1.310 0.0173 14.15 1.303 -0.0070 15.51 1.330 -0.0346 16.12 1.353 -0.0425 17.28 1.363 -0.0575 18.31 1.281 -0.0695 19.11 1.092 -0.0955 16.54 0.874 -0.0956 17.05 0.878 -0.0946 14.75 0.882 -0.0934 14.17 0.878 -0.0877 13.13 0.912 -0.0792 13.25 1.302 0.0200 11.26 1.154 0.0264 10.42 1.070 0.0280 9.26 0.953 0.0300 8.42 0.862 0.0314 7.18 0.724 0.0329 6.30 0.635 0.0350 4.99 0.493 0.0365 4.08 0.389 0.0377 3.14 0.282 0.0388 2.19 0.173 0.0399 0.92 0.003 0.0456 0.04 -0.083 0.0455 -0.94 -0.166 0.0400 -1.96 -0.279 0.0403 -2.99 -0.386 0.0394 -4.06 -0.485 0.0374 -5.25 -0.608 0.0308 Tabulated from data in file AB01096.DAT & reduced using program Q06.01L File ESA.LFT created on 10-24-1997 at 19:34:41 using program FORMAT