XFOIL Version 6.96 Calculated polar for: GOE 770 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -19.750 -1.0039 0.09661 0.09258 -0.0461 1.0000 0.0334 -19.500 -1.0238 0.08987 0.08567 -0.0500 1.0000 0.0336 -19.250 -1.0281 0.08587 0.08162 -0.0518 1.0000 0.0339 -19.000 -1.0295 0.08225 0.07795 -0.0535 1.0000 0.0342 -18.750 -1.0311 0.07861 0.07427 -0.0553 1.0000 0.0344 -18.500 -1.0334 0.07487 0.07046 -0.0573 1.0000 0.0347 -18.250 -1.0361 0.07116 0.06667 -0.0591 1.0000 0.0350 -18.000 -1.0396 0.06745 0.06287 -0.0609 1.0000 0.0353 -17.750 -1.0428 0.06386 0.05919 -0.0626 1.0000 0.0356 -17.500 -1.0456 0.06044 0.05566 -0.0641 1.0000 0.0359 -17.250 -1.0471 0.05728 0.05239 -0.0653 1.0000 0.0363 -17.000 -1.0483 0.05425 0.04925 -0.0664 1.0000 0.0366 -16.750 -1.0487 0.05139 0.04627 -0.0673 1.0000 0.0369 -16.500 -1.0481 0.04869 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0.00393 -0.0368 0.5205 0.5236 -2.250 0.0623 0.01046 0.00393 -0.0368 0.5172 0.5361 -2.000 0.0911 0.01056 0.00396 -0.0369 0.5133 0.5470 -1.750 0.1199 0.01051 0.00396 -0.0369 0.5104 0.5567 -1.500 0.1492 0.01053 0.00394 -0.0370 0.5069 0.5647 -1.250 0.1779 0.01048 0.00393 -0.0371 0.5034 0.5730 -1.000 0.2068 0.01050 0.00392 -0.0372 0.5001 0.5812 -0.750 0.2358 0.01057 0.00392 -0.0373 0.4965 0.5884 -0.500 0.2644 0.01058 0.00396 -0.0374 0.4931 0.5969 -0.250 0.2934 0.01058 0.00398 -0.0375 0.4895 0.6051 0.000 0.3224 0.01056 0.00396 -0.0376 0.4855 0.6119 0.250 0.3510 0.01054 0.00395 -0.0377 0.4816 0.6182 0.500 0.3798 0.01059 0.00395 -0.0379 0.4775 0.6244 0.750 0.4088 0.01065 0.00398 -0.0381 0.4738 0.6298 1.000 0.4376 0.01061 0.00400 -0.0382 0.4698 0.6357 1.250 0.4662 0.01060 0.00401 -0.0383 0.4656 0.6424 1.500 0.4947 0.01064 0.00402 -0.0385 0.4614 0.6497 1.750 0.5229 0.01071 0.00407 -0.0385 0.4570 0.6575 2.000 0.5513 0.01069 0.00413 -0.0386 0.4529 0.6662 2.250 0.5798 0.01071 0.00416 -0.0388 0.4481 0.6751 2.500 0.6074 0.01072 0.00420 -0.0388 0.4434 0.6854 2.750 0.6351 0.01081 0.00427 -0.0388 0.4386 0.6972 3.000 0.6627 0.01078 0.00435 -0.0388 0.4337 0.7111 3.250 0.6900 0.01080 0.00442 -0.0387 0.4286 0.7274 3.500 0.7165 0.01087 0.00451 -0.0385 0.4238 0.7473 3.750 0.7430 0.01089 0.00465 -0.0383 0.4192 0.7708 4.000 0.7692 0.01090 0.00478 -0.0380 0.4143 0.7990 4.250 0.7945 0.01095 0.00491 -0.0374 0.4095 0.8315 4.500 0.8186 0.01107 0.00508 -0.0367 0.4048 0.8664 4.750 0.8445 0.01112 0.00526 -0.0362 0.4006 0.8997 5.000 0.8731 0.01125 0.00545 -0.0363 0.3960 0.9293 5.250 0.9068 0.01146 0.00565 -0.0376 0.3914 0.9514 5.500 0.9430 0.01174 0.00589 -0.0395 0.3868 0.9676 5.750 0.9803 0.01192 0.00611 -0.0417 0.3826 0.9801 6.000 1.0210 0.01216 0.00633 -0.0446 0.3783 0.9872 6.250 1.0601 0.01244 0.00656 -0.0473 0.3743 0.9935 6.500 1.1004 0.01275 0.00683 -0.0504 0.3704 0.9981 6.750 1.1293 0.01293 0.00705 -0.0510 0.3675 1.0000 7.000 1.1474 0.01310 0.00723 -0.0494 0.3647 1.0000 7.250 1.1660 0.01330 0.00743 -0.0479 0.3619 1.0000 7.500 1.1846 0.01353 0.00763 -0.0465 0.3590 1.0000 7.750 1.2033 0.01384 0.00789 -0.0451 0.3555 1.0000 8.000 1.2226 0.01406 0.00813 -0.0438 0.3525 1.0000 8.250 1.2423 0.01425 0.00838 -0.0426 0.3494 1.0000 8.500 1.2626 0.01449 0.00863 -0.0416 0.3465 1.0000 8.750 1.2827 0.01476 0.00889 -0.0405 0.3436 1.0000 9.000 1.3026 0.01509 0.00919 -0.0395 0.3406 1.0000 9.250 1.3234 0.01546 0.00955 -0.0387 0.3374 1.0000 9.500 1.3417 0.01571 0.00987 -0.0374 0.3349 1.0000 9.750 1.3587 0.01599 0.01020 -0.0360 0.3319 1.0000 10.000 1.3755 0.01631 0.01055 -0.0345 0.3289 1.0000 10.250 1.3924 0.01670 0.01093 -0.0333 0.3258 1.0000 10.500 1.4108 0.01719 0.01138 -0.0323 0.3223 1.0000 10.750 1.4277 0.01761 0.01188 -0.0312 0.3198 1.0000 11.000 1.4438 0.01807 0.01241 -0.0301 0.3170 1.0000 11.250 1.4601 0.01858 0.01297 -0.0291 0.3140 1.0000 11.500 1.4759 0.01916 0.01358 -0.0282 0.3111 1.0000 11.750 1.4914 0.01982 0.01423 -0.0273 0.3079 1.0000 12.000 1.5073 0.02051 0.01493 -0.0266 0.3047 1.0000 12.250 1.5208 0.02129 0.01583 -0.0258 0.3019 1.0000 12.500 1.5342 0.02216 0.01676 -0.0252 0.2986 1.0000 12.750 1.5467 0.02313 0.01777 -0.0245 0.2950 1.0000 13.000 1.5580 0.02420 0.01883 -0.0238 0.2912 1.0000 13.250 1.5695 0.02535 0.02005 -0.0233 0.2879 1.0000 13.500 1.5800 0.02664 0.02145 -0.0230 0.2843 1.0000 13.750 1.5889 0.02807 0.02294 -0.0226 0.2802 1.0000 14.000 1.5952 0.02971 0.02457 -0.0222 0.2758 1.0000 14.250 1.6021 0.03141 0.02636 -0.0219 0.2717 1.0000 14.500 1.6074 0.03332 0.02836 -0.0217 0.2665 1.0000 14.750 1.6079 0.03559 0.03064 -0.0214 0.2610 1.0000 15.000 1.6098 0.03784 0.03296 -0.0212 0.2556 1.0000 15.250 1.6090 0.04038 0.03556 -0.0210 0.2492 1.0000 15.500 1.6053 0.04317 0.03837 -0.0207 0.2435 1.0000 15.750 1.6047 0.04581 0.04109 -0.0206 0.2366 1.0000 16.000 1.5962 0.04920 0.04449 -0.0204 0.2296 1.0000 16.250 1.5905 0.05243 0.04778 -0.0204 0.2213 1.0000 16.500 1.5790 0.05629 0.05165 -0.0204 0.2130 1.0000 16.750 1.5635 0.06064 0.05600 -0.0205 0.2037 1.0000 17.000 1.5509 0.06475 0.06012 -0.0206 0.1947 1.0000 17.250 1.5351 0.06928 0.06465 -0.0208 0.1866 1.0000 17.500 1.5185 0.07395 0.06932 -0.0211 0.1788 1.0000 17.750 1.5057 0.07827 0.07367 -0.0215 0.1722 1.0000 18.000 1.4907 0.08292 0.07832 -0.0220 0.1658 1.0000 18.250 1.4819 0.08687 0.08230 -0.0225 0.1601 1.0000