XFOIL Version 6.96 Calculated polar for: GOE 548 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 ------ -------- --------- --------- -------- -------- -------- -11.500 -0.6669 0.05611 0.05362 -0.0693 1.0000 0.0122 -11.250 -0.6929 0.05222 0.04967 -0.0695 1.0000 0.0122 -11.000 -0.7191 0.04973 0.04709 -0.0672 1.0000 0.0121 -10.750 -0.7456 0.04613 0.04332 -0.0667 0.9986 0.0121 -10.500 -0.7566 0.04212 0.03901 -0.0676 0.9940 0.0120 -10.250 -0.7642 0.03740 0.03388 -0.0673 0.9884 0.0121 -10.000 -0.7622 0.03239 0.02838 -0.0677 0.9848 0.0122 -9.750 -0.7452 0.03116 0.02709 -0.0677 0.9822 0.0128 -9.500 -0.7302 0.02982 0.02558 -0.0668 0.9783 0.0134 -9.250 -0.7091 0.02828 0.02385 -0.0670 0.9756 0.0139 -9.000 -0.6880 0.02602 0.02128 -0.0673 0.9735 0.0144 -8.750 -0.6645 0.02384 0.01878 -0.0676 0.9721 0.0150 -8.500 -0.6495 0.02233 0.01704 -0.0658 0.9683 0.0153 -8.250 -0.6280 0.02120 0.01571 -0.0651 0.9651 0.0159 -8.000 -0.6057 0.01925 0.01352 -0.0648 0.9627 0.0166 -7.750 -0.5776 0.01823 0.01242 -0.0655 0.9610 0.0180 -7.500 -0.5456 0.01773 0.01187 -0.0668 0.9598 0.0193 -7.250 -0.5128 0.01714 0.01118 -0.0681 0.9588 0.0209 -7.000 -0.4974 0.01630 0.01024 -0.0659 0.9541 0.0222 -6.750 -0.4725 0.01556 0.00948 -0.0656 0.9510 0.0243 -6.500 -0.4405 0.01512 0.00899 -0.0667 0.9491 0.0269 -6.250 -0.4084 0.01440 0.00820 -0.0679 0.9476 0.0303 -6.000 -0.3728 0.01401 0.00783 -0.0698 0.9466 0.0348 -5.750 -0.3362 0.01368 0.00743 -0.0718 0.9458 0.0385 -5.500 -0.3021 0.01287 0.00660 -0.0736 0.9449 0.0448 -5.250 -0.2861 0.01266 0.00635 -0.0711 0.9384 0.0481 -5.000 -0.2530 0.01214 0.00576 -0.0725 0.9363 0.0516 -4.750 -0.2196 0.01156 0.00516 -0.0739 0.9343 0.0577 -4.500 -0.1839 0.01118 0.00471 -0.0757 0.9327 0.0624 -4.250 -0.1479 0.01066 0.00421 -0.0776 0.9310 0.0718 -4.000 -0.1279 0.01032 0.00394 -0.0759 0.9238 0.0885 -3.750 -0.0986 0.00936 0.00347 -0.0767 0.9193 0.2090 -3.250 -0.0471 0.00841 0.00302 -0.0762 0.9070 0.3563 -3.000 -0.0156 0.00808 0.00282 -0.0771 0.9028 0.4106 -2.750 0.0046 0.00786 0.00274 -0.0754 0.8949 0.4548 -2.500 0.0326 0.00760 0.00261 -0.0755 0.8895 0.5073 -2.250 0.0542 0.00742 0.00254 -0.0741 0.8816 0.5486 -2.000 0.0806 0.00721 0.00243 -0.0737 0.8751 0.5917 -1.750 0.1024 0.00706 0.00237 -0.0723 0.8666 0.6266 -1.500 0.1286 0.00688 0.00227 -0.0718 0.8598 0.6623 -1.250 0.1493 0.00672 0.00223 -0.0701 0.8500 0.6979 -1.000 0.1729 0.00656 0.00218 -0.0690 0.8417 0.7402 -0.750 0.1956 0.00640 0.00215 -0.0677 0.8322 0.7852 -0.500 0.2192 0.00631 0.00214 -0.0666 0.8217 0.8173 -0.250 0.2448 0.00623 0.00208 -0.0658 0.8097 0.8434 0.000 0.2715 0.00618 0.00204 -0.0654 0.7973 0.8672 0.250 0.3013 0.00617 0.00201 -0.0656 0.7838 0.8885 0.500 0.3337 0.00621 0.00202 -0.0664 0.7713 0.9094 0.750 0.3717 0.00633 0.00208 -0.0685 0.7584 0.9277 1.250 0.4495 0.00666 0.00228 -0.0732 0.7338 0.9507 1.500 0.4858 0.00681 0.00239 -0.0750 0.7216 0.9577 1.750 0.5236 0.00698 0.00251 -0.0772 0.7110 0.9629 2.000 0.5565 0.00714 0.00263 -0.0783 0.7007 0.9702 2.250 0.5953 0.00728 0.00273 -0.0808 0.6883 0.9739 2.500 0.6304 0.00741 0.00284 -0.0824 0.6732 0.9798 2.750 0.6663 0.00752 0.00295 -0.0843 0.6585 0.9848 3.000 0.7039 0.00761 0.00302 -0.0866 0.6360 0.9895 3.250 0.7372 0.00784 0.00307 -0.0879 0.5860 0.9953 3.500 0.7739 0.00815 0.00316 -0.0902 0.5363 1.0000 3.750 0.7844 0.00841 0.00327 -0.0868 0.5034 1.0000 4.000 0.7920 0.00878 0.00342 -0.0828 0.4572 1.0000 4.250 0.7996 0.00921 0.00361 -0.0789 0.4036 1.0000 4.500 0.8062 0.00974 0.00384 -0.0748 0.3400 1.0000 4.750 0.8063 0.01064 0.00425 -0.0696 0.2405 1.0000 5.000 0.8128 0.01135 0.00465 -0.0656 0.1826 1.0000 5.250 0.8228 0.01193 0.00500 -0.0622 0.1384 1.0000 5.500 0.8285 0.01272 0.00543 -0.0581 0.0809 1.0000 5.750 0.8360 0.01344 0.00589 -0.0543 0.0319 1.0000 6.000 0.8486 0.01391 0.00634 -0.0512 0.0242 1.0000 6.250 0.8616 0.01428 0.00678 -0.0483 0.0222 1.0000 6.500 0.8747 0.01465 0.00722 -0.0454 0.0211 1.0000 6.750 0.8851 0.01521 0.00783 -0.0421 0.0191 1.0000 7.000 0.8939 0.01590 0.00861 -0.0385 0.0177 1.0000 7.250 0.9062 0.01645 0.00921 -0.0357 0.0174 1.0000 7.500 0.9188 0.01702 0.00985 -0.0330 0.0167 1.0000 7.750 0.9299 0.01770 0.01060 -0.0301 0.0162 1.0000 8.000 0.9406 0.01845 0.01140 -0.0272 0.0159 1.0000 8.250 0.9506 0.01929 0.01230 -0.0243 0.0154 1.0000 8.500 0.9605 0.02021 0.01327 -0.0215 0.0150 1.0000 8.750 0.9713 0.02114 0.01424 -0.0190 0.0144 1.0000 9.000 0.9818 0.02216 0.01530 -0.0166 0.0139 1.0000 9.250 0.9902 0.02397 0.01712 -0.0141 0.0131 1.0000 9.500 1.0110 0.02581 0.01898 -0.0133 0.0129 1.0000 9.750 1.0414 0.02778 0.02100 -0.0139 0.0128 1.0000 10.000 1.0521 0.02855 0.02192 -0.0115 0.0125 1.0000