XFOIL Version 6.94 Calculated polar for: Dayton-Wright T-1 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.080 Re = 0.300 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- 0.000 0.7185 0.00959 0.00419 -0.1039 0.6009 0.9858 0.500 0.7977 0.00980 0.00433 -0.1094 0.5855 1.0000 1.000 0.8400 0.01007 0.00439 -0.1071 0.5545 1.0000 1.500 0.8765 0.01063 0.00456 -0.1036 0.4989 1.0000 2.000 0.9174 0.01094 0.00479 -0.1011 0.4768 1.0000 2.500 0.9444 0.01174 0.00509 -0.0959 0.4141 1.0000 3.000 0.9816 0.01230 0.00550 -0.0928 0.3807 1.0000 3.500 1.0106 0.01311 0.00594 -0.0882 0.3488 1.0000 4.000 1.0444 0.01405 0.00672 -0.0847 0.3162 1.0000 4.500 1.0923 0.01511 0.00790 -0.0841 0.2986 1.0000 5.500 1.1799 0.01594 0.00883 -0.0813 0.2937 1.0000 6.000 1.2150 0.01599 0.00887 -0.0783 0.2879 1.0000 6.500 1.2502 0.01647 0.00928 -0.0756 0.2726 1.0000 7.000 1.2849 0.01731 0.01002 -0.0730 0.2557 1.0000 8.000 1.2735 0.02272 0.01443 -0.0575 0.1231 1.0000 8.500 1.2650 0.02705 0.01808 -0.0512 0.0412 1.0000 9.000 1.2772 0.02984 0.02078 -0.0477 0.0211 1.0000 9.500 1.2827 0.03332 0.02430 -0.0442 0.0177 1.0000 10.000 1.3021 0.03611 0.02726 -0.0421 0.0154 1.0000 10.500 1.3177 0.03940 0.03082 -0.0401 0.0144 1.0000 11.000 1.3159 0.04474 0.03647 -0.0382 0.0141 1.0000 11.500 1.3168 0.05003 0.04204 -0.0369 0.0140 1.0000 12.000 1.3034 0.05748 0.04979 -0.0364 0.0141 1.0000 12.500 1.2940 0.06436 0.05693 -0.0361 0.0143 1.0000 13.000 1.2769 0.07294 0.06577 -0.0368 0.0146 1.0000 13.500 1.2711 0.08050 0.07367 -0.0383 0.0148 1.0000 14.000 1.2662 0.08759 0.08100 -0.0390 0.0153 1.0000 14.500 1.2557 0.09577 0.08946 -0.0403 0.0160 1.0000 15.000 1.2329 0.10649 0.10052 -0.0432 0.0168 1.0000 15.500 1.2257 0.11344 0.10798 -0.0427 0.0192 1.0000 16.000 1.1952 0.12449 0.11966 -0.0449 0.0214 1.0000 16.500 1.1432 0.14168 0.13722 -0.0544 0.0213 1.0000 17.000 1.0861 0.16067 0.15675 -0.0618 0.0231 1.0000 17.500 1.0835 0.17199 0.16839 -0.0661 0.0314 1.0000 19.000 0.9435 0.26584 0.26226 -0.0897 0.0482 1.0000 19.500 0.9449 0.27770 0.27412 -0.0936 0.0479 1.0000 20.000 0.9498 0.28597 0.28238 -0.1001 0.0408 1.0000 20.500 0.9541 0.29533 0.29174 -0.1031 0.0332 1.0000 21.000 0.9651 0.30065 0.29706 -0.1044 0.0288 1.0000