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 = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -18.250 -0.8925 0.11893 0.11656 -0.0365 1.0000 0.0112 -18.000 -0.9416 0.10433 0.10176 -0.0445 1.0000 0.0111 -17.750 -0.9727 0.09403 0.09128 -0.0503 1.0000 0.0110 -17.500 -0.9967 0.08560 0.08269 -0.0551 1.0000 0.0110 -17.250 -1.0141 0.07865 0.07560 -0.0589 1.0000 0.0110 -17.000 -1.0273 0.07268 0.06949 -0.0622 1.0000 0.0110 -16.750 -1.0388 0.06724 0.06392 -0.0650 1.0000 0.0111 -16.500 -1.0467 0.06251 0.05906 -0.0674 1.0000 0.0111 -16.250 -1.0523 0.05833 0.05476 -0.0694 1.0000 0.0112 -16.000 -1.0561 0.05456 0.05088 -0.0709 1.0000 0.0112 -15.750 -1.0550 0.05155 0.04777 -0.0722 1.0000 0.0113 -15.500 -1.0533 0.04876 0.04487 -0.0732 1.0000 0.0114 -15.250 -1.0502 0.04630 0.04232 -0.0739 1.0000 0.0115 -15.000 -1.0563 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0.8629 0.01179 0.00490 -0.1111 0.0882 0.7248 4.250 0.8903 0.01198 0.00509 -0.1111 0.0858 0.7270 4.500 0.9173 0.01220 0.00530 -0.1110 0.0827 0.7290 4.750 0.9434 0.01245 0.00553 -0.1107 0.0790 0.7310 5.000 0.9693 0.01272 0.00582 -0.1103 0.0758 0.7329 5.250 0.9961 0.01289 0.00602 -0.1102 0.0745 0.7348 5.500 1.0227 0.01309 0.00623 -0.1100 0.0726 0.7367 5.750 1.0490 0.01331 0.00647 -0.1097 0.0705 0.7386 6.000 1.0749 0.01357 0.00671 -0.1094 0.0683 0.7408 6.250 1.1001 0.01391 0.00704 -0.1090 0.0656 0.7428 6.500 1.1261 0.01415 0.00729 -0.1087 0.0643 0.7444 6.750 1.1521 0.01432 0.00750 -0.1084 0.0628 0.7464 7.000 1.1775 0.01456 0.00776 -0.1080 0.0613 0.7479 7.250 1.2023 0.01484 0.00803 -0.1075 0.0596 0.7495 7.500 1.2264 0.01518 0.00837 -0.1069 0.0572 0.7512 7.750 1.2504 0.01552 0.00874 -0.1063 0.0554 0.7530 8.000 1.2756 0.01574 0.00900 -0.1059 0.0543 0.7547 8.250 1.3004 0.01598 0.00927 -0.1054 0.0526 0.7565 8.500 1.3245 0.01628 0.00957 -0.1048 0.0504 0.7582 8.750 1.3475 0.01668 0.00995 -0.1041 0.0475 0.7596 9.000 1.3718 0.01691 0.01023 -0.1035 0.0461 0.7613 9.250 1.3952 0.01718 0.01053 -0.1028 0.0436 0.7632 9.500 1.4175 0.01753 0.01088 -0.1019 0.0408 0.7649 9.750 1.4393 0.01792 0.01128 -0.1009 0.0386 0.7664 10.000 1.4604 0.01833 0.01170 -0.0999 0.0366 0.7679 10.250 1.4805 0.01880 0.01217 -0.0986 0.0346 0.7694 10.500 1.5004 0.01924 0.01265 -0.0973 0.0332 0.7709 10.750 1.5197 0.01966 0.01312 -0.0959 0.0320 0.7724 11.000 1.5356 0.02013 0.01362 -0.0939 0.0305 0.7740 11.250 1.5512 0.02069 0.01420 -0.0918 0.0289 0.7754 11.500 1.5683 0.02125 0.01480 -0.0902 0.0277 0.7769 11.750 1.5854 0.02180 0.01540 -0.0885 0.0266 0.7786 12.000 1.6015 0.02244 0.01608 -0.0868 0.0253 0.7800 12.250 1.6161 0.02320 0.01688 -0.0849 0.0239 0.7814 12.500 1.6323 0.02381 0.01756 -0.0832 0.0229 0.7829 12.750 1.6487 0.02440 0.01822 -0.0816 0.0218 0.7844 13.000 1.6635 0.02514 0.01900 -0.0799 0.0201 0.7859 13.250 1.6766 0.02599 0.01989 -0.0780 0.0186 0.7875 13.500 1.6895 0.02689 0.02083 -0.0761 0.0172 0.7890 13.750 1.7005 0.02793 0.02190 -0.0741 0.0158 0.7904 14.000 1.7121 0.02892 0.02296 -0.0721 0.0150 0.7916 14.250 1.7222 0.03004 0.02414 -0.0701 0.0140 0.7932 14.500 1.7302 0.03133 0.02551 -0.0680 0.0132 0.7949 14.750 1.7378 0.03266 0.02693 -0.0659 0.0125 0.7966 15.000 1.7465 0.03391 0.02828 -0.0640 0.0120 0.7982 15.250 1.7535 0.03533 0.02978 -0.0621 0.0114 0.7998 15.500 1.7586 0.03694 0.03149 -0.0601 0.0110 0.8015 15.750 1.7616 0.03876 0.03339 -0.0581 0.0105 0.8031 16.000 1.7615 0.04094 0.03567 -0.0560 0.0100 0.8048 16.250 1.7648 0.04283 0.03766 -0.0544 0.0098 0.8064 16.500 1.7666 0.04490 0.03984 -0.0529 0.0096 0.8080 16.750 1.7671 0.04717 0.04223 -0.0515 0.0092 0.8099 17.000 1.7652 0.04978 0.04495 -0.0502 0.0091 0.8115 17.250 1.7620 0.05263 0.04792 -0.0492 0.0089 0.8131 17.500 1.7559 0.05595 0.05136 -0.0484 0.0087 0.8147 17.750 1.7487 0.05961 0.05514 -0.0480 0.0085 0.8165 18.000 1.7381 0.06396 0.05964 -0.0482 0.0085 0.8182 18.250 1.7242 0.06905 0.06486 -0.0490 0.0082 0.8199 18.500 1.7074 0.07495 0.07092 -0.0506 0.0082 0.8212 18.750 1.6856 0.08210 0.07825 -0.0534 0.0081 0.8223 19.000 1.6551 0.09132 0.08767 -0.0577 0.0080 0.8233 19.250 1.6176 0.10238 0.09895 -0.0636 0.0081 0.8240