XFOIL Version 6.94 Calculated polar for: dae41 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 0.3110 0.00844 0.00364 -0.0589 0.7272 0.9459 0.500 0.4007 0.00841 0.00344 -0.0653 0.7114 0.9836 1.000 0.4799 0.00836 0.00326 -0.0703 0.6931 1.0000 1.500 0.5255 0.00838 0.00318 -0.0682 0.6736 1.0000 2.000 0.5736 0.00848 0.00314 -0.0666 0.6536 1.0000 2.500 0.6231 0.00868 0.00320 -0.0651 0.6325 1.0000 3.000 0.6736 0.00890 0.00331 -0.0639 0.6095 1.0000 3.500 0.7248 0.00912 0.00347 -0.0628 0.5845 1.0000 4.000 0.7761 0.00940 0.00365 -0.0617 0.5585 1.0000 4.500 0.8273 0.00971 0.00391 -0.0607 0.5296 1.0000 5.000 0.8778 0.01011 0.00423 -0.0597 0.4990 1.0000 5.500 0.9271 0.01059 0.00462 -0.0584 0.4649 1.0000 6.000 0.9753 0.01112 0.00507 -0.0571 0.4232 1.0000 6.500 1.0204 0.01185 0.00562 -0.0554 0.3773 1.0000 7.000 1.0645 0.01267 0.00632 -0.0536 0.3295 1.0000 7.500 1.1051 0.01369 0.00716 -0.0514 0.2801 1.0000 8.000 1.1425 0.01488 0.00814 -0.0488 0.2328 1.0000 8.500 1.1771 0.01616 0.00927 -0.0459 0.1896 1.0000 9.000 1.2065 0.01761 0.01056 -0.0424 0.1525 1.0000 9.500 1.2276 0.01917 0.01200 -0.0376 0.1213 1.0000 10.000 1.2456 0.02102 0.01378 -0.0329 0.0962 1.0000 10.500 1.2603 0.02329 0.01601 -0.0286 0.0794 1.0000 11.000 1.2754 0.02578 0.01855 -0.0250 0.0678 1.0000 11.500 1.2879 0.02869 0.02156 -0.0217 0.0597 1.0000 12.000 1.2934 0.03240 0.02530 -0.0186 0.0533 1.0000 12.500 1.3088 0.03554 0.02864 -0.0165 0.0490 1.0000 13.000 1.3170 0.03946 0.03266 -0.0147 0.0450 1.0000 13.500 1.3238 0.04383 0.03719 -0.0131 0.0420 1.0000 14.000 1.3336 0.04809 0.04166 -0.0121 0.0395 1.0000 14.500 1.3413 0.05278 0.04648 -0.0116 0.0374 1.0000 15.000 1.3480 0.05797 0.05178 -0.0106 0.0353 1.0000 15.500 1.3530 0.06351 0.05763 -0.0110 0.0342 1.0000 16.000 1.3541 0.06983 0.06424 -0.0121 0.0328 1.0000 16.500 1.3528 0.07679 0.07147 -0.0138 0.0316 1.0000 17.000 1.3493 0.08436 0.07926 -0.0162 0.0306 1.0000 17.500 1.3438 0.09252 0.08766 -0.0191 0.0298 1.0000 18.000 1.3318 0.10210 0.09751 -0.0229 0.0292 1.0000 18.500 1.3034 0.11513 0.11091 -0.0292 0.0288 1.0000 19.000 1.2654 0.13106 0.12724 -0.0386 0.0287 1.0000 19.500 1.2209 0.14985 0.14643 -0.0511 0.0288 1.0000