XFOIL Version 6.94 Calculated polar for: FX 75-193 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 ------- -------- --------- --------- -------- ------- ------- 0.500 0.4229 0.02584 0.02039 -0.0951 0.7216 0.7235 2.000 0.4466 0.02871 0.02335 -0.0761 0.6795 0.7392 2.500 0.5051 0.02828 0.02288 -0.0777 0.6730 0.7437 3.000 0.5741 0.02761 0.02217 -0.0807 0.6698 0.7482 3.500 0.6403 0.02661 0.02120 -0.0830 0.6675 0.7520 4.000 0.7066 0.02520 0.01981 -0.0847 0.6659 0.7549 4.500 0.8216 0.02017 0.01475 -0.0908 0.6649 0.7584 5.000 0.8569 0.02170 0.01642 -0.0894 0.6632 0.7632 5.500 0.9587 0.01705 0.01153 -0.0942 0.6301 0.7666 6.000 0.9754 0.01849 0.01308 -0.0898 0.6157 0.7704 6.500 1.0192 0.01850 0.01292 -0.0885 0.5792 0.7748 7.000 1.0369 0.01977 0.01383 -0.0839 0.5167 0.7769 7.500 1.0226 0.02257 0.01612 -0.0755 0.4367 0.7784 8.000 1.0465 0.02373 0.01733 -0.0724 0.4093 0.7806 8.500 0.9284 0.03318 0.02498 -0.0542 0.1468 0.7819 9.000 0.9770 0.03345 0.02561 -0.0544 0.1712 0.7839 9.500 0.9371 0.04007 0.03132 -0.0465 0.0172 0.7850 10.000 0.9683 0.04178 0.03309 -0.0455 0.0189 0.7867 10.500 0.9909 0.04433 0.03583 -0.0436 0.0159 0.7881 11.000 1.0124 0.04703 0.03867 -0.0420 0.0140 0.7897 11.500 1.0382 0.04948 0.04125 -0.0410 0.0138 0.7905 12.000 1.0442 0.05386 0.04595 -0.0386 0.0142 0.7909 12.500 1.0650 0.05695 0.04917 -0.0378 0.0151 0.7912 13.000 1.0741 0.06138 0.05380 -0.0363 0.0145 0.7927 13.500 1.0946 0.06471 0.05722 -0.0359 0.0137 0.7934 14.000 1.0998 0.06980 0.06253 -0.0349 0.0142 0.7929 14.500 1.1074 0.07474 0.06770 -0.0342 0.0142 0.7928 15.000 1.1211 0.07892 0.07203 -0.0340 0.0141 0.7926 15.500 1.1331 0.08271 0.07604 -0.0322 0.0150 0.7923 16.000 1.1519 0.08615 0.07966 -0.0317 0.0151 0.7922 16.500 1.1770 0.08875 0.08253 -0.0301 0.0158 0.7921 17.000 1.1702 0.09678 0.09051 -0.0346 0.0118 0.7921 17.500 1.1992 0.09834 0.09265 -0.0309 0.0154 0.7921 18.000 1.1791 0.10778 0.10189 -0.0367 0.0093 0.7918 19.000 1.1918 0.11873 0.11395 -0.0366 0.0143 0.7916 19.500 1.1790 0.12684 0.12189 -0.0420 0.0098 0.7917 20.000 1.1921 0.13229 0.12774 -0.0446 0.0120 0.7926 20.500 1.1514 0.14492 0.14064 -0.0519 0.0097 0.7931 21.000 1.1221 0.15820 0.15430 -0.0600 0.0096 0.7930 21.500 1.1150 0.16817 0.16448 -0.0666 0.0098 0.7928 22.000 1.1213 0.17581 0.17224 -0.0720 0.0101 0.7933