XFOIL Version 6.94 Calculated polar for: DFVLR R-4 AIRFOIL 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 0.3885 0.01326 0.00834 -0.1035 0.8968 0.7278 0.500 0.4444 0.01271 0.00784 -0.1016 0.8775 0.7325 1.000 0.5005 0.01251 0.00769 -0.1006 0.8613 0.7391 1.500 0.5641 0.01218 0.00735 -0.1020 0.8389 0.7488 2.000 0.6138 0.01195 0.00715 -0.0994 0.8035 0.7536 2.500 0.6637 0.01192 0.00701 -0.0971 0.7329 0.7595 3.000 0.6943 0.01387 0.00737 -0.0921 0.4244 0.7683 3.500 0.7204 0.01593 0.00832 -0.0868 0.2065 0.7740 4.000 0.7619 0.01706 0.00915 -0.0842 0.1513 0.7804 4.500 0.8134 0.01793 0.00990 -0.0839 0.1313 0.7870 5.000 0.8621 0.01874 0.01069 -0.0830 0.1192 0.7925 5.500 0.9044 0.01969 0.01162 -0.0804 0.1105 0.7981 6.000 0.9535 0.02052 0.01250 -0.0795 0.1037 0.8033 7.000 1.0547 0.02266 0.01471 -0.0787 0.0928 0.8129 7.500 1.1016 0.02398 0.01613 -0.0774 0.0881 0.8176 8.000 1.1498 0.02504 0.01727 -0.0764 0.0829 0.8223 8.500 1.1986 0.02639 0.01877 -0.0758 0.0771 0.8275 9.000 1.2468 0.02785 0.02024 -0.0753 0.0717 0.8319 9.500 1.2850 0.02875 0.02140 -0.0726 0.0668 0.8361 10.000 1.3238 0.03026 0.02310 -0.0703 0.0623 0.8410 10.500 1.3589 0.03150 0.02432 -0.0677 0.0577 0.8454 11.000 1.3815 0.03256 0.02574 -0.0630 0.0534 0.8496 11.500 1.4074 0.03413 0.02752 -0.0593 0.0496 0.8541 12.000 1.4308 0.03560 0.02909 -0.0556 0.0461 0.8586 13.000 1.4682 0.04032 0.03441 -0.0486 0.0390 0.8670 14.000 1.4888 0.04717 0.04180 -0.0424 0.0332 0.8748 14.500 1.4907 0.05160 0.04632 -0.0397 0.0311 0.8796 15.000 1.4803 0.05803 0.05326 -0.0378 0.0292 0.8845 15.500 1.4717 0.06474 0.06018 -0.0376 0.0277 0.8887 16.000 1.4500 0.07406 0.06981 -0.0391 0.0266 0.8923 16.500 1.4160 0.08675 0.08301 -0.0441 0.0260 0.8961 17.000 1.3738 0.10273 0.09945 -0.0528 0.0255 0.8998 17.500 1.3153 0.12382 0.12101 -0.0660 0.0256 0.9025 18.000 1.1763 0.16811 0.16589 -0.0963 0.0270 0.8992 19.500 0.7017 0.22435 0.22225 -0.0942 0.0360 0.8758 20.000 0.7043 0.23127 0.22920 -0.0972 0.0350 0.8791 20.500 0.7090 0.23747 0.23543 -0.1002 0.0321 0.8831 21.000 0.7247 0.24243 0.24043 -0.1009 0.0310 0.8878 21.500 0.7207 0.25040 0.24842 -0.1060 0.0282 0.8902 22.000 0.7317 0.25521 0.25328 -0.1073 0.0271 0.8949 22.500 0.7309 0.26355 0.26164 -0.1113 0.0253 0.8986 23.000 0.7380 0.26924 0.26736 -0.1136 0.0238 0.9045 24.000 0.7472 0.28304 0.28123 -0.1190 0.0218 0.9165 24.500 0.7529 0.28894 0.28717 -0.1213 0.0205 0.9250 25.000 0.7608 0.29378 0.29207 -0.1225 0.0198 0.9405