XFOIL Version 6.96 Calculated polar for: USA 27 mod. AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -8.000 -0.3654 0.11352 0.10733 -0.0238 1.0000 0.1573 -7.750 -0.3995 0.11321 0.10717 -0.0219 1.0000 0.1579 -7.500 -0.4233 0.11183 0.10589 -0.0216 1.0000 0.1583 -7.250 -0.4208 0.10817 0.10231 -0.0197 1.0000 0.1588 -6.750 -0.3947 0.09031 0.08414 -0.0326 0.9878 0.0852 -6.250 -0.3688 0.07693 0.07035 -0.0456 0.9703 0.0750 -6.000 -0.3512 0.07282 0.06612 -0.0483 0.9624 0.0746 -5.750 -0.3338 0.06876 0.06190 -0.0506 0.9542 0.0742 -5.500 -0.3115 0.06461 0.05756 -0.0535 0.9470 0.0735 -5.250 -0.2945 0.06085 0.05358 -0.0548 0.9378 0.0724 -5.000 -0.2685 0.05643 0.04882 -0.0578 0.9313 0.0711 -4.750 -0.2512 0.05262 0.04464 -0.0584 0.9211 0.0700 -4.500 -0.2228 0.04863 0.04011 -0.0605 0.9144 0.0690 -4.250 -0.1993 0.04555 0.03654 -0.0609 0.9040 0.0684 -4.000 -0.1702 0.04294 0.03344 -0.0618 0.8943 0.0686 -3.750 -0.1349 0.04072 0.03077 -0.0635 0.8854 0.0700 -3.500 -0.1069 0.03896 0.02862 -0.0636 0.8736 0.0714 -3.250 -0.0713 0.03720 0.02642 -0.0649 0.8646 0.0724 -3.000 -0.0383 0.03574 0.02463 -0.0655 0.8543 0.0730 -2.750 -0.0083 0.03460 0.02321 -0.0656 0.8433 0.0738 -2.500 0.0325 0.03334 0.02165 -0.0673 0.8359 0.0749 -2.250 0.0606 0.03248 0.02069 -0.0670 0.8237 0.0762 -2.000 0.1008 0.03145 0.01959 -0.0688 0.8156 0.0791 -1.750 0.1354 0.03072 0.01872 -0.0696 0.8047 0.0835 -1.500 0.1664 0.03009 0.01798 -0.0696 0.7931 0.0881 -1.250 0.2082 0.02913 0.01699 -0.0715 0.7854 0.0947 -1.000 0.2343 0.02862 0.01652 -0.0707 0.7719 0.1026 -0.750 0.2624 0.02800 0.01612 -0.0704 0.7594 0.1251 -0.500 0.2948 0.02730 0.01586 -0.0707 0.7487 0.2386 -0.250 0.3250 0.02689 0.01556 -0.0706 0.7366 0.3194 0.000 0.3490 0.02642 0.01524 -0.0696 0.7225 0.3873 0.250 0.3740 0.02572 0.01475 -0.0688 0.7092 0.4421 0.500 0.5067 0.02423 0.01428 -0.0878 0.6967 1.0000 0.750 0.5378 0.02409 0.01383 -0.0878 0.6824 1.0000 1.000 0.5697 0.02397 0.01341 -0.0880 0.6683 1.0000 1.250 0.6008 0.02392 0.01307 -0.0881 0.6539 1.0000 1.500 0.6272 0.02403 0.01294 -0.0876 0.6387 1.0000 1.750 0.6526 0.02422 0.01291 -0.0869 0.6239 1.0000 2.000 0.6775 0.02446 0.01294 -0.0861 0.6099 1.0000 2.250 0.7032 0.02471 0.01300 -0.0856 0.5968 1.0000 2.500 0.7304 0.02496 0.01304 -0.0853 0.5846 1.0000 2.750 0.7488 0.02540 0.01338 -0.0836 0.5715 1.0000 3.000 0.7702 0.02580 0.01367 -0.0825 0.5601 1.0000 3.250 0.7964 0.02611 0.01383 -0.0821 0.5503 1.0000 3.500 0.8131 0.02664 0.01432 -0.0802 0.5395 1.0000 3.750 0.8377 0.02699 0.01456 -0.0796 0.5308 1.0000 4.000 0.8556 0.02751 0.01505 -0.0780 0.5213 1.0000 4.250 0.8789 0.02793 0.01538 -0.0772 0.5134 1.0000 4.500 0.8972 0.02848 0.01593 -0.0757 0.5052 1.0000 4.750 0.9230 0.02887 0.01623 -0.0754 0.4987 1.0000 5.000 0.9378 0.02955 0.01695 -0.0733 0.4907 1.0000 5.250 0.9640 0.02992 0.01723 -0.0730 0.4842 1.0000 5.500 0.9777 0.03065 0.01803 -0.0709 0.4765 1.0000 5.750 1.0005 0.03108 0.01841 -0.0700 0.4694 1.0000 6.000 1.0161 0.03173 0.01907 -0.0681 0.4615 1.0000 6.250 1.0364 0.03215 0.01947 -0.0668 0.4532 1.0000 6.500 1.0503 0.03278 0.02012 -0.0647 0.4446 1.0000 6.750 1.0710 0.03318 0.02047 -0.0634 0.4362 1.0000 7.000 1.0831 0.03391 0.02125 -0.0611 0.4279 1.0000 7.250 1.1018 0.03446 0.02183 -0.0597 0.4205 1.0000 7.500 1.1196 0.03515 0.02255 -0.0583 0.4141 1.0000 7.750 1.1292 0.03608 0.02359 -0.0557 0.4069 1.0000 8.000 1.1566 0.03645 0.02394 -0.0557 0.4008 1.0000 8.250 1.1574 0.03771 0.02538 -0.0520 0.3938 1.0000 8.500 1.1726 0.03850 0.02624 -0.0503 0.3873 1.0000 8.750 1.1929 0.03917 0.02693 -0.0494 0.3813 1.0000 9.000 1.1869 0.04064 0.02860 -0.0449 0.3744 1.0000 9.250 1.2088 0.04117 0.02918 -0.0441 0.3680 1.0000 9.500 1.2070 0.04262 0.03076 -0.0405 0.3614 1.0000 9.750 1.2080 0.04399 0.03226 -0.0374 0.3543 1.0000 10.000 1.2378 0.04416 0.03241 -0.0375 0.3482 1.0000 10.250 1.2093 0.04709 0.03561 -0.0317 0.3409 1.0000 10.500 1.2251 0.04790 0.03650 -0.0304 0.3345 1.0000 10.750 1.2228 0.04986 0.03860 -0.0278 0.3284 1.0000 11.000 1.1971 0.05353 0.04246 -0.0240 0.3213 1.0000 11.250 1.2283 0.05336 0.04232 -0.0238 0.3162 1.0000 11.500 1.1534 0.06183 0.05104 -0.0194 0.3073 1.0000 11.750 1.1591 0.06372 0.05301 -0.0184 0.3016 1.0000 12.250 1.0831 0.07834 0.06782 -0.0180 0.2845 1.0000 12.500 1.1226 0.07607 0.06562 -0.0165 0.2825 1.0000 12.750 1.0230 0.09404 0.08365 -0.0208 0.2680 1.0000