XFOIL Version 6.96 Calculated polar for: GOE 683 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -15.000 -0.6867 0.07271 0.06593 -0.0800 1.0000 0.0736 -14.750 -0.7395 0.06386 0.05676 -0.0845 1.0000 0.0737 -14.500 -0.7713 0.05856 0.05121 -0.0858 1.0000 0.0740 -14.250 -0.7955 0.05462 0.04703 -0.0855 1.0000 0.0744 -14.000 -0.8165 0.05141 0.04359 -0.0841 1.0000 0.0750 -13.750 -0.8349 0.04882 0.04076 -0.0818 1.0000 0.0755 -13.500 -0.8398 0.04691 0.03876 -0.0796 1.0000 0.0762 -13.250 -0.8324 0.04561 0.03751 -0.0780 1.0000 0.0771 -13.000 -0.8304 0.04429 0.03619 -0.0758 1.0000 0.0781 -12.750 -0.8317 0.04298 0.03485 -0.0730 1.0000 0.0790 -12.500 -0.8348 0.04174 0.03355 -0.0698 1.0000 0.0798 -12.250 -0.8405 0.04064 0.03238 -0.0660 1.0000 0.0808 -12.000 -0.8499 0.03978 0.03145 -0.0613 1.0000 0.0815 -11.750 -0.8276 0.03798 0.02943 -0.0625 0.9867 0.0831 -11.500 -0.8039 0.03644 0.02775 -0.0635 0.9721 0.0848 -11.250 -0.7756 0.03521 0.02657 -0.0649 0.9590 0.0866 -11.000 -0.7471 0.03397 0.02530 -0.0664 0.9471 0.0886 -10.750 -0.7171 0.03269 0.02390 -0.0680 0.9355 0.0908 -10.500 -0.6846 0.03142 0.02242 -0.0700 0.9247 0.0933 -10.250 -0.6481 0.03023 0.02128 -0.0727 0.9153 0.0957 -10.000 -0.6160 0.02922 0.02022 -0.0745 0.9027 0.0986 -9.750 -0.5818 0.02821 0.01907 -0.0766 0.8909 0.1018 -9.500 -0.5496 0.02728 0.01809 -0.0782 0.8783 0.1050 -9.250 -0.5245 0.02657 0.01733 -0.0783 0.8636 0.1084 -9.000 -0.4992 0.02590 0.01653 -0.0784 0.8499 0.1125 -8.750 -0.4748 0.02527 0.01584 -0.0782 0.8375 0.1164 -8.500 -0.4567 0.02479 0.01531 -0.0767 0.8233 0.1211 -8.250 -0.4365 0.02429 0.01474 -0.0756 0.8111 0.1268 -8.000 -0.4167 0.02383 0.01422 -0.0743 0.7996 0.1332 -7.750 -0.3999 0.02342 0.01378 -0.0724 0.7875 0.1405 -7.500 -0.3789 0.02300 0.01325 -0.0712 0.7779 0.1500 -7.250 -0.3653 0.02266 0.01294 -0.0687 0.7664 0.1590 -7.000 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-2.000 0.0617 0.01837 0.00872 -0.0376 0.5977 0.4971 -1.750 0.0894 0.01819 0.00876 -0.0375 0.5897 0.5448 -1.500 0.1258 0.01797 0.00873 -0.0390 0.5828 0.6033 -1.250 0.1745 0.01793 0.00890 -0.0428 0.5753 0.6672 -1.000 0.2389 0.01823 0.00936 -0.0494 0.5668 0.7248 -0.750 0.3026 0.01877 0.00988 -0.0555 0.5601 0.7661 -0.500 0.3451 0.01931 0.01046 -0.0577 0.5516 0.7947 -0.250 0.3759 0.01968 0.01075 -0.0577 0.5452 0.8218 0.000 0.4073 0.02011 0.01108 -0.0578 0.5395 0.8442 0.250 0.4349 0.02056 0.01151 -0.0574 0.5325 0.8648 0.500 0.4647 0.02093 0.01179 -0.0574 0.5264 0.8826 0.750 0.4954 0.02127 0.01201 -0.0577 0.5210 0.8975 1.000 0.5230 0.02166 0.01239 -0.0576 0.5142 0.9115 1.250 0.5537 0.02198 0.01264 -0.0580 0.5083 0.9243 1.500 0.5977 0.02226 0.01278 -0.0611 0.5033 0.9349 1.750 0.6373 0.02261 0.01316 -0.0634 0.4962 0.9475 2.000 0.6762 0.02281 0.01328 -0.0657 0.4902 0.9580 2.250 0.7115 0.02293 0.01329 -0.0674 0.4856 0.9665 2.500 0.7475 0.02300 0.01338 -0.0694 0.4796 0.9728 2.750 0.7790 0.02315 0.01351 -0.0705 0.4739 0.9803 3.000 0.8182 0.02303 0.01330 -0.0731 0.4689 0.9857 3.250 0.8535 0.02309 0.01332 -0.0750 0.4641 0.9921 3.500 0.8912 0.02302 0.01329 -0.0776 0.4583 0.9982 3.750 0.9153 0.02313 0.01336 -0.0773 0.4535 1.0000 4.000 0.9340 0.02330 0.01346 -0.0759 0.4497 1.0000 4.250 0.9510 0.02355 0.01370 -0.0742 0.4457 1.0000 4.500 0.9653 0.02389 0.01411 -0.0721 0.4410 1.0000 4.750 0.9815 0.02418 0.01440 -0.0702 0.4367 1.0000 5.000 0.9996 0.02441 0.01460 -0.0687 0.4328 1.0000 5.250 1.0202 0.02463 0.01474 -0.0675 0.4296 1.0000 5.500 1.0319 0.02508 0.01529 -0.0650 0.4251 1.0000 5.750 1.0453 0.02549 0.01576 -0.0627 0.4207 1.0000 6.000 1.0612 0.02580 0.01607 -0.0608 0.4165 1.0000 6.250 1.0801 0.02605 0.01628 -0.0593 0.4129 1.0000 6.500 1.0956 0.02642 0.01665 -0.0574 0.4090 1.0000 6.750 1.1033 0.02697 0.01732 -0.0542 0.4042 1.0000 7.000 1.1152 0.02736 0.01774 -0.0517 0.3994 1.0000 7.250 1.1317 0.02763 0.01798 -0.0498 0.3955 1.0000 7.500 1.1499 0.02791 0.01822 -0.0483 0.3919 1.0000 7.750 1.1513 0.02863 0.01909 -0.0442 0.3875 1.0000 8.000 1.1571 0.02920 0.01973 -0.0408 0.3833 1.0000 8.250 1.1680 0.02962 0.02017 -0.0381 0.3795 1.0000 8.500 1.1846 0.02992 0.02046 -0.0364 0.3763 1.0000 8.750 1.1921 0.03045 0.02102 -0.0333 0.3728 1.0000 9.000 1.1796 0.03129 0.02200 -0.0270 0.3688 1.0000 9.250 1.1734 0.03199 0.02277 -0.0219 0.3650 1.0000 9.500 1.1781 0.03252 0.02333 -0.0185 0.3615 1.0000 9.750 1.1933 0.03281 0.02361 -0.0166 0.3584 1.0000 10.000 1.1950 0.03357 0.02442 -0.0131 0.3553 1.0000 10.250 1.1724 0.03523 0.02624 -0.0070 0.3514 1.0000 10.500 1.1622 0.03666 0.02777 -0.0029 0.3474 1.0000 10.750 1.1681 0.03742 0.02856 -0.0004 0.3435 1.0000 11.000 1.1899 0.03746 0.02856 0.0005 0.3403 1.0000 11.250 1.1592 0.04027 0.03155 0.0055 0.3356 1.0000 11.500 1.1292 0.04354 0.03497 0.0096 0.3302 1.0000 11.750 1.1362 0.04452 0.03597 0.0113 0.3262 1.0000 12.000 1.1658 0.04390 0.03529 0.0118 0.3231 1.0000 12.250 1.0591 0.05450 0.04621 0.0167 0.3134 1.0000 12.500 1.0756 0.05473 0.04644 0.0178 0.3094 1.0000 12.750 1.1107 0.05326 0.04494 0.0185 0.3069 1.0000 13.000 0.9876 0.06859 0.06052 0.0196 0.2927 1.0000 13.250 1.0209 0.06687 0.05879 0.0207 0.2911 1.0000 13.500 1.0585 0.06473 0.05665 0.0218 0.2897 1.0000 13.750 0.9669 0.07836 0.07044 0.0208 0.2747 1.0000 14.000 0.9993 0.07654 0.06863 0.0221 0.2735 1.0000 14.500 0.9639 0.08629 0.07852 0.0217 0.2576 1.0000