XFOIL Version 6.96 Calculated polar for: DFVLR R-4 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -19.750 -0.9366 0.13728 0.13482 -0.0259 1.0000 0.0080 -19.500 -1.0021 0.11970 0.11702 -0.0352 1.0000 0.0079 -19.250 -1.0562 0.10511 0.10221 -0.0429 1.0000 0.0078 -19.000 -1.0945 0.09397 0.09088 -0.0489 1.0000 0.0077 -18.750 -1.1213 0.08543 0.08218 -0.0535 1.0000 0.0077 -18.500 -1.1412 0.07832 0.07493 -0.0573 1.0000 0.0078 -18.250 -1.1548 0.07249 0.06898 -0.0603 1.0000 0.0078 -18.000 -1.1657 0.06727 0.06364 -0.0629 1.0000 0.0078 -17.750 -1.1741 0.06257 0.05882 -0.0652 1.0000 0.0079 -17.500 -1.1796 0.05844 0.05459 -0.0670 1.0000 0.0079 -17.250 -1.1825 0.05479 0.05084 -0.0686 1.0000 0.0080 -17.000 -1.1827 0.05160 0.04755 -0.0698 1.0000 0.0081 -16.750 -1.1821 0.04863 0.04449 -0.0708 1.0000 0.0082 -16.500 -1.1799 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0.6807 2.750 0.7274 0.01073 0.00363 -0.1123 0.0884 0.6832 3.000 0.7553 0.01088 0.00379 -0.1123 0.0858 0.6857 3.250 0.7829 0.01106 0.00395 -0.1123 0.0826 0.6885 3.500 0.8102 0.01126 0.00413 -0.1122 0.0787 0.6914 3.750 0.8377 0.01145 0.00430 -0.1122 0.0755 0.6943 4.000 0.8653 0.01162 0.00446 -0.1122 0.0735 0.6968 4.250 0.8925 0.01179 0.00464 -0.1121 0.0709 0.6989 4.500 0.9194 0.01200 0.00484 -0.1120 0.0679 0.7009 4.750 0.9461 0.01222 0.00505 -0.1118 0.0649 0.7030 5.000 0.9729 0.01243 0.00526 -0.1116 0.0629 0.7052 5.250 0.9995 0.01265 0.00547 -0.1115 0.0609 0.7073 5.500 1.0258 0.01289 0.00570 -0.1112 0.0588 0.7093 5.750 1.0519 0.01314 0.00594 -0.1110 0.0569 0.7113 6.000 1.0781 0.01338 0.00618 -0.1107 0.0555 0.7132 6.250 1.1043 0.01358 0.00642 -0.1104 0.0546 0.7151 6.500 1.1302 0.01380 0.00668 -0.1101 0.0531 0.7168 6.750 1.1558 0.01406 0.00694 -0.1098 0.0510 0.7183 7.000 1.1810 0.01434 0.00722 -0.1094 0.0491 0.7200 7.250 1.2059 0.01463 0.00752 -0.1089 0.0472 0.7218 7.500 1.2312 0.01487 0.00780 -0.1085 0.0458 0.7234 7.750 1.2560 0.01515 0.00808 -0.1080 0.0429 0.7251 8.000 1.2800 0.01549 0.00839 -0.1074 0.0391 0.7267 8.250 1.3038 0.01585 0.00873 -0.1067 0.0363 0.7282 8.500 1.3270 0.01622 0.00911 -0.1060 0.0335 0.7299 8.750 1.3500 0.01659 0.00950 -0.1052 0.0307 0.7317 9.000 1.3722 0.01702 0.00994 -0.1043 0.0282 0.7333 9.250 1.3945 0.01742 0.01036 -0.1034 0.0268 0.7348 9.500 1.4163 0.01785 0.01081 -0.1025 0.0257 0.7361 9.750 1.4375 0.01830 0.01128 -0.1014 0.0246 0.7375 10.000 1.4583 0.01876 0.01176 -0.1003 0.0235 0.7389 10.250 1.4792 0.01915 0.01219 -0.0991 0.0230 0.7403 10.500 1.4994 0.01955 0.01264 -0.0979 0.0223 0.7418 10.750 1.5184 0.01999 0.01313 -0.0964 0.0209 0.7432 11.000 1.5337 0.02053 0.01368 -0.0943 0.0187 0.7444 11.250 1.5492 0.02112 0.01430 -0.0923 0.0170 0.7458 11.500 1.5652 0.02176 0.01497 -0.0905 0.0156 0.7471 11.750 1.5816 0.02237 0.01563 -0.0887 0.0147 0.7484 12.000 1.5972 0.02306 0.01636 -0.0869 0.0136 0.7497 12.250 1.6120 0.02379 0.01714 -0.0850 0.0127 0.7511 12.500 1.6274 0.02447 0.01789 -0.0833 0.0121 0.7525 12.750 1.6419 0.02523 0.01870 -0.0814 0.0113 0.7539 13.000 1.6554 0.02606 0.01959 -0.0795 0.0105 0.7553 13.250 1.6679 0.02696 0.02054 -0.0776 0.0098 0.7566 13.500 1.6806 0.02786 0.02150 -0.0757 0.0093 0.7580 13.750 1.6920 0.02885 0.02255 -0.0737 0.0086 0.7593 14.000 1.7027 0.02991 0.02368 -0.0717 0.0082 0.7607 14.250 1.7125 0.03105 0.02490 -0.0697 0.0077 0.7623 14.500 1.7222 0.03219 0.02612 -0.0678 0.0075 0.7638 14.750 1.7311 0.03342 0.02743 -0.0658 0.0072 0.7652 15.000 1.7392 0.03473 0.02883 -0.0639 0.0070 0.7666 15.250 1.7459 0.03618 0.03037 -0.0620 0.0067 0.7682 15.500 1.7517 0.03772 0.03201 -0.0602 0.0066 0.7699 15.750 1.7557 0.03947 0.03384 -0.0583 0.0063 0.7716 16.000 1.7591 0.04132 0.03579 -0.0565 0.0061 0.7732 16.250 1.7609 0.04335 0.03791 -0.0548 0.0060 0.7745 16.500 1.7625 0.04546 0.04012 -0.0533 0.0059 0.7758 16.750 1.7628 0.04776 0.04253 -0.0519 0.0057 0.7771 17.000 1.7619 0.05027 0.04516 -0.0507 0.0056 0.7787 17.250 1.7593 0.05307 0.04808 -0.0497 0.0055 0.7803 17.500 1.7549 0.05621 0.05134 -0.0490 0.0055 0.7819 17.750 1.7486 0.05976 0.05502 -0.0487 0.0053 0.7835 18.000 1.7409 0.06371 0.05911 -0.0487 0.0053 0.7850 18.250 1.7290 0.06847 0.06401 -0.0494 0.0051 0.7863 18.500 1.7160 0.07371 0.06940 -0.0507 0.0052 0.7876 18.750 1.6975 0.08017 0.07602 -0.0530 0.0051 0.7887 19.000 1.6722 0.08826 0.08429 -0.0565 0.0050 0.7896 19.250 1.6387 0.09834 0.09459 -0.0617 0.0050 0.7903