Description of the Data Format ********************************************************************** Annotated polar file: ********************************************************************** Airfoil: E387 (C) <--- AIRFOIL NAME Builder: J. Robertson <--- MODEL BUILDER Comment: clean; used to validate against LTPT data <--- COMMENT Number of Reynolds #'s: 2 <--- NUMBER OF DIFFERENT REYNOLDS NUMBERS FOR THIS AIRFOIL Average Reynolds #: 59700 <--- AVERAGE REYNOLDS NUMBER OF THIS RUN Number of angles of attack: 17 <--- NUMBER OF ANGLES OF ATTACK IN THIS RUN alpha / Cl / Cd / Spanwise Cd's >>> -6.16 -0.356 0.0657 0.0542 0.0561 0.0761 0.0764 <--- ANGLE OF ATTACK, LIFT COEFFICIENT, AVERAGE DRAG COEFFICIENT, SPANWISE DRAG COEFFICIENTS USED TO GET AVERAGE DRAG COEFFICIENT -5.07 -0.284 0.0551 0.0423 0.0456 0.0585 0.0739 -4.06 -0.200 0.0340 0.0298 0.0338 0.0368 0.0356 -3.05 -0.104 0.0268 0.0247 0.0269 0.0261 0.0294 -2.05 0.021 0.0193 0.0207 0.0204 0.0156 0.0206 -0.95 0.165 0.0185 0.0195 0.0181 0.0165 0.0200 0.06 0.270 0.0230 0.0223 0.0190 0.0239 0.0267 1.09 0.378 0.0255 0.0271 0.0260 0.0251 0.0239 2.08 0.487 0.0291 0.0342 0.0296 0.0257 0.0269 3.13 0.570 0.0340 0.0359 0.0311 0.0336 0.0353 4.18 0.626 0.0415 0.0455 0.0409 0.0413 0.0383 5.12 0.679 0.0503 0.0531 0.0512 0.0469 0.0498 6.18 0.765 0.0580 0.0621 0.0592 0.0533 0.0575 7.18 0.913 0.0516 0.0508 0.0474 0.0519 0.0565 8.24 1.104 0.0362 0.0303 0.0358 0.0370 0.0419 9.27 1.199 0.0274 0.0246 0.0250 0.0292 0.0308 10.26 1.232 0.0318 0.0333 0.0292 0.0341 0.0308 Tabulated from data in file CL01573.DAT & reduced using program Q05.01D <--- RUN 1573 BY CHRIS LYON(CL), DATA REDUCED USING QUICKBASIC DRAG PROGRAM VERSION 5.01 Average Reynolds #: 459200 Number of angles of attack: 17 alpha / Cl / Cd / Spanwise Cd's >>> -5.12 -0.202 0.0455 0.0460 0.0438 0.0442 0.0479 -4.02 -0.079 0.0206 0.0186 0.0197 0.0213 0.0228 -3.01 0.017 0.0127 0.0125 0.0126 0.0127 0.0130 -2.05 0.118 0.0105 0.0106 0.0100 0.0107 0.0107 -1.01 0.229 0.0089 0.0089 0.0090 0.0089 0.0088 0.02 0.336 0.0071 0.0073 0.0073 0.0069 0.0069 1.07 0.458 0.0073 0.0071 0.0078 0.0072 0.0071 2.11 0.573 0.0079 0.0074 0.0085 0.0077 0.0078 3.13 0.682 0.0084 0.0077 0.0095 0.0082 0.0083 4.16 0.787 0.0090 0.0081 0.0101 0.0086 0.0090 5.20 0.893 0.0091 0.0084 0.0100 0.0088 0.0094 6.22 0.990 0.0093 0.0090 0.0095 0.0091 0.0096 7.29 1.084 0.0114 0.0110 0.0116 0.0115 0.0116 8.24 1.145 0.0149 0.0146 0.0156 0.0151 0.0145 9.42 1.210 0.0207 0.0200 0.0201 0.0212 0.0214 10.52 1.245 0.0269 0.0248 0.0258 0.0275 0.0295 11.55 1.245 0.0335 0.0255 0.0249 0.0273 0.0562 Tabulated from data in file CL01832.DAT & reduced using program Q05.01D File E387C.DRG created on 09-12-1997 at 13:39:49 using program FORMAT <--- NAME OF THIS FILE, DATE AND TIME IT WAS CREATED, PROGRAM IT WAS CREATED WITH ********************************************************************** Annotated lift and moment file: ********************************************************************** Airfoil: E387 (C) <--- AIRFOIL NAME Builder: J. Robertson <--- MODEL BUILDER Comment: clean; used to validate against LTPT data <--- COMMENT Number of Reynolds #'s: 2 <--- NUMBER OF DIFFERENT REYNOLDS NUMBERS FOR THIS AIRFOIL Average Reynolds #: 59900 <--- AVERAGE REYNOLDS NUMBER OF THIS RUN Number of angles of attack: 49 <--- NUMBER OF ANGLES OF ATTACK IN THIS RUN alpha / Cl / Cm -6.06 -0.336 -0.0199 <--- ANGLE OF ATTACK, LIFT COEFFICIENT, MOMENT COEFFICIENT -4.84 -0.253 -0.0467 -3.64 -0.158 -0.0615 -2.83 -0.081 -0.0656 -1.62 0.061 -0.0751 -0.44 0.227 -0.0837 0.46 0.316 -0.0870 1.63 0.434 -0.0913 2.45 0.504 -0.0947 3.65 0.580 -0.0972 4.49 0.631 -0.0982 5.70 0.728 -0.1017 6.54 0.808 -0.1000 7.78 1.021 -0.0866 8.63 1.124 -0.0759 9.79 1.200 -0.0656 10.56 1.223 -0.0595 11.71 1.240 -0.0529 12.83 1.247 -0.0494 13.58 1.222 -0.0487 14.78 1.110 -0.1161 15.57 1.048 -0.1288 16.79 1.060 -0.1465 17.63 1.049 -0.1519 18.46 1.056 -0.1551 16.95 1.056 -0.1489 15.80 1.087 -0.1400 15.01 1.143 -0.1255 13.93 1.212 -0.0617 12.91 1.248 -0.0483 11.86 1.248 -0.0496 10.82 1.245 -0.0565 10.01 1.219 -0.0631 8.92 1.165 -0.0729 7.80 1.058 -0.0849 6.98 0.949 -0.0981 5.83 0.752 -0.1028 4.71 0.664 -0.1015 3.59 0.599 -0.1008 2.81 0.548 -0.1042 1.72 0.453 -0.1032 0.63 0.326 -0.0944 -0.43 0.243 -0.0889 -1.20 0.158 -0.0838 -2.29 0.009 -0.0721 -3.34 -0.101 -0.0639 -4.40 -0.190 -0.0586 -5.46 -0.272 -0.0419 -6.60 -0.360 -0.0123 Tabulated from data in file CL01572.DAT & reduced using program Q06.01L <--- RUN 1572 BY CHRIS LYON(CL), DATA REDUCED USING QUICKBASIC LIFT PROGRAM VERSION 6.01 Average Reynolds #: 461900 Number of angles of attack: 49 alpha / Cl / Cm -6.17 -0.337 -0.0354 -4.76 -0.157 -0.0726 -3.77 -0.048 -0.0745 -2.72 0.054 -0.0750 -1.74 0.157 -0.0755 -0.75 0.261 -0.0763 0.35 0.375 -0.0762 1.51 0.500 -0.0766 2.41 0.596 -0.0767 3.62 0.722 -0.0771 4.57 0.819 -0.0772 5.62 0.926 -0.0773 6.67 1.025 -0.0759 7.40 1.081 -0.0744 8.52 1.152 -0.0706 9.67 1.214 -0.0655 10.53 1.241 -0.0611 11.73 1.244 -0.0616 12.54 1.246 -0.0644 13.61 1.234 -0.0710 14.65 1.296 -0.0824 14.94 1.313 -0.0965 15.93 1.320 -0.1505 16.99 1.316 -0.1609 18.44 1.330 -0.1682 16.90 1.291 -0.1555 15.73 1.314 -0.1444 15.21 1.332 -0.1098 13.92 1.253 -0.0740 12.68 1.264 -0.0671 11.81 1.256 -0.0615 10.64 1.252 -0.0587 9.67 1.218 -0.0632 8.62 1.160 -0.0679 7.56 1.092 -0.0717 6.59 1.013 -0.0743 5.58 0.918 -0.0756 4.59 0.817 -0.0757 3.63 0.719 -0.0763 2.69 0.619 -0.0761 1.81 0.527 -0.0762 0.53 0.388 -0.0759 -0.36 0.292 -0.0759 -1.52 0.169 -0.0748 -2.62 0.053 -0.0740 -3.31 -0.016 -0.0732 -4.49 -0.134 -0.0737 -5.51 -0.258 -0.0588 -6.37 -0.372 -0.0245 Tabulated from data in file CL01831.DAT & reduced using program Q06.01L File E387C.LFT created on 10-24-1997 at 19:34:41 using program FORMAT <--- NAME OF THIS FILE, DATE AND TIME IT WAS CREATED, PROGRAM IT WAS CREATED WITH