XFOIL Version 6.96 Calculated polar for: USA 48 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 ------ -------- --------- --------- -------- -------- -------- -11.500 -0.5132 0.08856 0.08129 -0.0642 1.0000 0.0588 -11.250 -0.5386 0.08181 0.07455 -0.0674 1.0000 0.0586 -11.000 -0.5636 0.07634 0.06906 -0.0693 1.0000 0.0582 -10.750 -0.5913 0.07172 0.06440 -0.0700 1.0000 0.0579 -10.500 -0.6194 0.06811 0.06076 -0.0690 1.0000 0.0576 -10.250 -0.6489 0.06544 0.05803 -0.0658 1.0000 0.0574 -10.000 -0.6748 0.06267 0.05514 -0.0622 1.0000 0.0574 -9.750 -0.6950 0.05976 0.05204 -0.0589 1.0000 0.0576 -9.500 -0.7117 0.05682 0.04884 -0.0554 1.0000 0.0579 -9.250 -0.7233 0.05396 0.04565 -0.0521 1.0000 0.0584 -9.000 -0.7291 0.05119 0.04257 -0.0491 1.0000 0.0591 -8.750 -0.7234 0.04914 0.04052 -0.0470 1.0000 0.0607 -8.500 -0.7186 0.04734 0.03862 -0.0447 1.0000 0.0628 -8.250 -0.7143 0.04529 0.03631 -0.0423 1.0000 0.0647 -8.000 -0.7083 0.04313 0.03376 -0.0399 1.0000 0.0666 -7.750 -0.6986 0.04126 0.03166 -0.0378 1.0000 0.0684 -7.500 -0.6874 0.04002 0.03043 -0.0359 1.0000 0.0711 -7.250 -0.6760 0.03871 0.02895 -0.0339 1.0000 0.0742 -7.000 -0.6632 0.03736 0.02736 -0.0319 1.0000 0.0771 -6.750 -0.6429 0.03631 0.02630 -0.0316 0.9975 0.0808 -6.500 -0.6091 0.03515 0.02479 -0.0334 0.9908 0.0867 -6.250 -0.5760 0.03404 0.02366 -0.0352 0.9840 0.0918 -6.000 -0.5437 0.03307 0.02246 -0.0365 0.9763 0.0991 -5.750 -0.5139 0.03201 0.02136 -0.0377 0.9684 0.1064 -5.500 -0.4820 0.03099 0.02022 -0.0391 0.9611 0.1150 -5.250 -0.4554 0.02987 0.01919 -0.0398 0.9522 0.1300 -5.000 -0.4289 0.02875 0.01845 -0.0406 0.9436 0.1598 -4.750 -0.3974 0.02801 0.01793 -0.0420 0.9358 0.2331 -4.500 -0.3718 0.02759 0.01760 -0.0423 0.9261 0.2900 -4.250 -0.3371 0.02735 0.01735 -0.0440 0.9191 0.3420 -4.000 -0.3130 0.02714 0.01708 -0.0437 0.9086 0.3737 -3.750 -0.2807 0.02690 0.01677 -0.0448 0.9012 0.4039 -3.500 -0.2547 0.02665 0.01654 -0.0447 0.8916 0.4345 -3.250 -0.2266 0.02639 0.01636 -0.0448 0.8834 0.4700 -3.000 -0.1989 0.02616 0.01625 -0.0447 0.8747 0.5040 -2.750 -0.1738 0.02607 0.01636 -0.0438 0.8659 0.5423 -2.500 -0.1460 0.02610 0.01659 -0.0430 0.8578 0.5875 -2.250 -0.1239 0.02623 0.01669 -0.0416 0.8481 0.6320 -2.000 -0.0930 0.02618 0.01651 -0.0418 0.8409 0.6741 -1.750 -0.0723 0.02621 0.01646 -0.0403 0.8305 0.7063 -1.500 -0.0389 0.02602 0.01617 -0.0407 0.8245 0.7379 -1.250 -0.0187 0.02603 0.01614 -0.0390 0.8141 0.7655 -1.000 0.0179 0.02579 0.01583 -0.0399 0.8086 0.7939 -0.750 0.0429 0.02585 0.01589 -0.0390 0.7985 0.8195 -0.500 0.0874 0.02569 0.01569 -0.0413 0.7933 0.8477 -0.250 0.1264 0.02584 0.01582 -0.0431 0.7844 0.8752 0.000 0.1871 0.02585 0.01575 -0.0488 0.7790 0.9018 0.250 0.2437 0.02590 0.01571 -0.0540 0.7724 0.9263 0.500 0.3015 0.02592 0.01565 -0.0597 0.7645 0.9453 0.750 0.3614 0.02571 0.01533 -0.0656 0.7582 0.9600 1.000 0.4092 0.02570 0.01526 -0.0698 0.7480 0.9755 1.250 0.4598 0.02555 0.01504 -0.0744 0.7388 0.9899 1.500 0.5044 0.02535 0.01478 -0.0778 0.7296 1.0000 1.750 0.5106 0.02547 0.01486 -0.0745 0.7175 1.0000 2.000 0.5322 0.02536 0.01469 -0.0736 0.7081 1.0000 2.500 0.5556 0.02572 0.01495 -0.0686 0.6858 1.0000 2.750 0.5887 0.02558 0.01473 -0.0694 0.6779 1.0000 3.000 0.5952 0.02604 0.01517 -0.0660 0.6656 1.0000 3.250 0.6134 0.02630 0.01540 -0.0645 0.6553 1.0000 3.500 0.6416 0.02635 0.01541 -0.0644 0.6463 1.0000 3.750 0.6537 0.02682 0.01589 -0.0619 0.6346 1.0000 4.000 0.6778 0.02699 0.01603 -0.0612 0.6246 1.0000 4.250 0.7039 0.02706 0.01609 -0.0607 0.6140 1.0000 4.750 0.7389 0.02761 0.01667 -0.0570 0.5889 1.0000 5.000 0.7643 0.02764 0.01668 -0.0562 0.5769 1.0000 5.250 0.7910 0.02765 0.01669 -0.0556 0.5649 1.0000 5.500 0.8053 0.02805 0.01712 -0.0534 0.5518 1.0000 5.750 0.8226 0.02838 0.01748 -0.0515 0.5391 1.0000 6.000 0.8441 0.02861 0.01773 -0.0503 0.5272 1.0000 6.250 0.8712 0.02869 0.01782 -0.0499 0.5158 1.0000 6.500 0.8820 0.02929 0.01850 -0.0472 0.5031 1.0000 6.750 0.8969 0.02980 0.01907 -0.0452 0.4913 1.0000 7.000 0.9172 0.03012 0.01943 -0.0439 0.4799 1.0000 7.250 0.9344 0.03051 0.01990 -0.0421 0.4682 1.0000 7.500 0.9421 0.03116 0.02064 -0.0391 0.4555 1.0000 7.750 0.9529 0.03171 0.02125 -0.0365 0.4426 1.0000 8.000 0.9665 0.03220 0.02179 -0.0343 0.4302 1.0000 8.250 0.9846 0.03256 0.02220 -0.0327 0.4186 1.0000 8.500 0.9912 0.03347 0.02324 -0.0300 0.4066 1.0000 8.750 1.0015 0.03427 0.02413 -0.0277 0.3950 1.0000 9.000 1.0164 0.03489 0.02482 -0.0260 0.3838 1.0000 9.250 1.0321 0.03546 0.02545 -0.0244 0.3723 1.0000 9.500 1.0386 0.03654 0.02668 -0.0220 0.3601 1.0000 9.750 1.0482 0.03752 0.02775 -0.0200 0.3481 1.0000 10.000 1.0600 0.03839 0.02869 -0.0182 0.3361 1.0000 10.250 1.0752 0.03912 0.02944 -0.0167 0.3245 1.0000 10.500 1.0797 0.04053 0.03098 -0.0146 0.3122 1.0000 10.750 1.0862 0.04194 0.03251 -0.0128 0.3010 1.0000 11.000 1.0963 0.04310 0.03375 -0.0112 0.2898 1.0000 11.250 1.1040 0.04430 0.03497 -0.0095 0.2779 1.0000 11.500 1.1002 0.04643 0.03725 -0.0076 0.2663 1.0000 11.750 1.0997 0.04833 0.03922 -0.0059 0.2549 1.0000 12.000 1.1003 0.05008 0.04099 -0.0044 0.2432 1.0000 12.250 1.0966 0.05243 0.04344 -0.0032 0.2321 1.0000 12.500 1.0921 0.05508 0.04621 -0.0023 0.2219 1.0000 12.750 1.0926 0.05719 0.04835 -0.0015 0.2121 1.0000 13.000 1.0874 0.06020 0.05156 -0.0011 0.2028 1.0000 13.250 1.0834 0.06313 0.05461 -0.0008 0.1936 1.0000 13.500 1.0806 0.06585 0.05735 -0.0005 0.1835 1.0000 13.750 1.0720 0.06955 0.06117 -0.0008 0.1728 1.0000 14.000 1.0635 0.07340 0.06513 -0.0013 0.1621 1.0000 14.250 1.0563 0.07712 0.06888 -0.0019 0.1509 1.0000 14.500 1.0493 0.08090 0.07262 -0.0025 0.1393 1.0000 14.750 1.0428 0.08464 0.07626 -0.0032 0.1281 1.0000 15.000 1.0332 0.08926 0.08099 -0.0044 0.1173 1.0000 15.250 1.0232 0.09412 0.08595 -0.0058 0.1067 1.0000 15.500 1.0140 0.09902 0.09092 -0.0073 0.0964 1.0000 15.750 1.0036 0.10444 0.09651 -0.0092 0.0863 1.0000