XFOIL Version 6.94 Calculated polar for: NN7 MK20 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.080 Re = 0.450 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- 0.000 0.4546 0.01125 0.00558 -0.1019 0.6618 0.6537 0.500 0.5118 0.01125 0.00558 -0.1026 0.6561 0.6576 1.000 0.5688 0.01127 0.00558 -0.1031 0.6487 0.6620 1.500 0.6244 0.01118 0.00550 -0.1033 0.6398 0.6681 2.000 0.6817 0.01138 0.00564 -0.1039 0.6301 0.6714 2.500 0.7373 0.01142 0.00578 -0.1041 0.6240 0.6754 3.000 0.7931 0.01143 0.00583 -0.1044 0.6146 0.6796 3.500 0.8495 0.01147 0.00582 -0.1049 0.6046 0.6833 4.000 0.9050 0.01159 0.00595 -0.1052 0.5930 0.6868 4.500 0.9594 0.01157 0.00603 -0.1052 0.5798 0.6896 5.000 1.0135 0.01168 0.00607 -0.1053 0.5639 0.6927 5.500 1.0661 0.01161 0.00614 -0.1050 0.5509 0.6968 6.000 1.1169 0.01184 0.00638 -0.1043 0.5321 0.7013 6.500 1.1656 0.01198 0.00660 -0.1033 0.5086 0.7054 7.000 1.2135 0.01229 0.00695 -0.1022 0.4848 0.7097 7.500 1.2555 0.01281 0.00740 -0.1002 0.4503 0.7140 8.000 1.2817 0.01388 0.00816 -0.0955 0.3858 0.7178 8.500 1.3111 0.01473 0.00902 -0.0915 0.3536 0.7208 9.000 1.2998 0.01753 0.01121 -0.0824 0.2544 0.7258 9.500 1.3081 0.01996 0.01348 -0.0772 0.2058 0.7307 10.000 1.3171 0.02274 0.01611 -0.0728 0.1660 0.7355 10.500 1.3169 0.02646 0.01957 -0.0684 0.1169 0.7401 11.000 1.3189 0.03033 0.02324 -0.0649 0.0816 0.7450 11.500 1.3301 0.03369 0.02660 -0.0624 0.0658 0.7489 12.000 1.3394 0.03727 0.03020 -0.0600 0.0506 0.7544 12.500 1.3081 0.04488 0.03746 -0.0560 0.0074 0.7592 13.000 1.3168 0.04920 0.04197 -0.0546 0.0064 0.7640 13.500 1.3324 0.05289 0.04587 -0.0537 0.0069 0.7694 14.000 1.3450 0.05713 0.05031 -0.0530 0.0070 0.7743 14.500 1.3264 0.06536 0.05889 -0.0519 0.0052 0.7777 15.000 1.3294 0.07126 0.06502 -0.0520 0.0053 0.7837 15.500 1.3100 0.08022 0.07433 -0.0524 0.0049 0.7887 16.000 1.3005 0.08794 0.08235 -0.0533 0.0048 0.7940 16.500 1.2896 0.09618 0.09086 -0.0546 0.0048 0.7993 17.500 1.2760 0.11230 0.10750 -0.0588 0.0048 0.8135 18.000 1.2757 0.11970 0.11516 -0.0615 0.0049 0.8256 18.500 1.2658 0.12865 0.12446 -0.0648 0.0049 0.8441 19.500 1.2466 0.14655 0.14304 -0.0732 0.0050 1.0000 20.000 1.2382 0.15557 0.15229 -0.0788 0.0051 1.0000 20.500 1.2218 0.16690 0.16391 -0.0858 0.0052 1.0000 21.000 1.2016 0.18039 0.17769 -0.0941 0.0054 1.0000 21.500 1.1766 0.19672 0.19432 -0.1037 0.0056 1.0000 22.000 1.1250 0.22457 0.22257 -0.1182 0.0060 1.0000 24.000 1.0350 0.33472 0.33276 -0.1521 0.0131 1.0000 24.500 1.0402 0.34579 0.34385 -0.1556 0.0122 1.0000 25.000 1.0449 0.35638 0.35446 -0.1589 0.0114 1.0000 25.500 1.0486 0.36613 0.36423 -0.1616 0.0108 1.0000 26.000 1.0510 0.37504 0.37316 -0.1636 0.0104 1.0000 27.000 0.8505 0.35289 0.35126 -0.1381 0.0096 1.0000 27.500 0.8392 0.35334 0.35175 -0.1385 0.0096 1.0000 28.000 0.8307 0.35422 0.35268 -0.1393 0.0096 1.0000 28.500 0.8207 0.35601 0.35447 -0.1400 0.0095 1.0000 29.000 0.8147 0.35747 0.35596 -0.1410 0.0095 1.0000 29.500 0.8096 0.35965 0.35818 -0.1425 0.0095 1.0000 30.000 0.8093 0.36545 0.36401 -0.1457 0.0074 1.0000 30.500 0.8059 0.36684 0.36542 -0.1472 0.0062 1.0000 31.000 0.8010 0.36859 0.36719 -0.1483 0.0083 1.0000