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 = 0.500 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -17.750 -0.8676 0.11632 0.11315 -0.0378 1.0000 0.0111 -17.500 -0.9066 0.10361 0.10025 -0.0447 1.0000 0.0110 -17.250 -0.9346 0.09372 0.09018 -0.0503 1.0000 0.0110 -17.000 -0.9561 0.08558 0.08187 -0.0549 1.0000 0.0110 -16.750 -0.9733 0.07860 0.07473 -0.0588 1.0000 0.0110 -16.500 -0.9869 0.07252 0.06849 -0.0621 1.0000 0.0111 -16.250 -0.9976 0.06722 0.06303 -0.0648 1.0000 0.0111 -16.000 -1.0059 0.06246 0.05812 -0.0671 1.0000 0.0111 -15.750 -1.0113 0.05834 0.05386 -0.0689 1.0000 0.0112 -15.500 -1.0153 0.05462 0.05000 -0.0704 1.0000 0.0113 -15.250 -1.0175 0.05129 0.04653 -0.0715 1.0000 0.0113 -15.000 -1.0179 0.04837 0.04348 -0.0722 1.0000 0.0114 -14.750 -1.0170 0.04578 0.04076 -0.0726 1.0000 0.0115 -14.500 -1.0185 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-0.1129 0.7846 0.6673 0.000 0.4338 0.00750 0.00245 -0.1128 0.7592 0.6703 0.250 0.4612 0.00764 0.00248 -0.1125 0.7279 0.6740 0.500 0.4846 0.00807 0.00253 -0.1114 0.6422 0.6784 0.750 0.5034 0.00897 0.00280 -0.1098 0.5135 0.6825 1.000 0.5252 0.00966 0.00310 -0.1087 0.4201 0.6853 1.250 0.5486 0.01025 0.00336 -0.1080 0.3442 0.6881 1.500 0.5728 0.01080 0.00360 -0.1075 0.2748 0.6911 1.750 0.5983 0.01124 0.00381 -0.1073 0.2248 0.6944 2.000 0.6244 0.01164 0.00400 -0.1071 0.1859 0.6977 2.250 0.6503 0.01196 0.00422 -0.1068 0.1603 0.6998 2.500 0.6766 0.01225 0.00443 -0.1066 0.1410 0.7022 2.750 0.7031 0.01253 0.00465 -0.1064 0.1252 0.7047 3.000 0.7297 0.01280 0.00485 -0.1062 0.1135 0.7077 3.250 0.7566 0.01307 0.00506 -0.1061 0.1046 0.7110 3.500 0.7835 0.01330 0.00528 -0.1060 0.0991 0.7139 3.750 0.8097 0.01354 0.00553 -0.1057 0.0943 0.7160 4.000 0.8357 0.01381 0.00579 -0.1054 0.0899 0.7181 4.250 0.8622 0.01405 0.00604 -0.1052 0.0871 0.7201 4.500 0.8886 0.01428 0.00629 -0.1050 0.0839 0.7221 4.750 0.9147 0.01455 0.00655 -0.1048 0.0805 0.7244 5.000 0.9406 0.01486 0.00684 -0.1045 0.0776 0.7271 5.250 0.9663 0.01515 0.00714 -0.1041 0.0754 0.7292 5.500 0.9919 0.01539 0.00744 -0.1037 0.0738 0.7309 5.750 1.0173 0.01566 0.00775 -0.1033 0.0720 0.7324 6.000 1.0424 0.01595 0.00807 -0.1029 0.0702 0.7341 6.250 1.0672 0.01626 0.00840 -0.1024 0.0682 0.7360 6.500 1.0916 0.01661 0.00875 -0.1019 0.0663 0.7381 6.750 1.1158 0.01698 0.00914 -0.1013 0.0647 0.7400 7.000 1.1404 0.01730 0.00951 -0.1008 0.0636 0.7420 7.250 1.1648 0.01763 0.00988 -0.1003 0.0623 0.7440 7.500 1.1884 0.01796 0.01025 -0.0996 0.0606 0.7455 7.750 1.2116 0.01832 0.01063 -0.0989 0.0585 0.7470 8.000 1.2336 0.01877 0.01108 -0.0979 0.0561 0.7486 8.250 1.2567 0.01911 0.01148 -0.0972 0.0545 0.7504 8.500 1.2795 0.01945 0.01190 -0.0964 0.0527 0.7523 8.750 1.3019 0.01982 0.01232 -0.0955 0.0504 0.7541 9.000 1.3234 0.02026 0.01275 -0.0946 0.0479 0.7559 9.250 1.3452 0.02063 0.01317 -0.0937 0.0456 0.7575 9.500 1.3667 0.02100 0.01358 -0.0927 0.0423 0.7591 9.750 1.3867 0.02144 0.01402 -0.0915 0.0391 0.7605 10.000 1.4038 0.02190 0.01451 -0.0897 0.0366 0.7619 10.250 1.4204 0.02243 0.01506 -0.0879 0.0346 0.7634 10.500 1.4379 0.02299 0.01568 -0.0863 0.0330 0.7650 10.750 1.4555 0.02358 0.01634 -0.0848 0.0314 0.7665 11.000 1.4727 0.02421 0.01704 -0.0833 0.0296 0.7681 11.250 1.4890 0.02492 0.01779 -0.0817 0.0281 0.7696 11.500 1.5053 0.02562 0.01856 -0.0801 0.0270 0.7712 11.750 1.5209 0.02638 0.01938 -0.0785 0.0258 0.7728 12.000 1.5356 0.02722 0.02027 -0.0768 0.0246 0.7743 12.250 1.5492 0.02814 0.02124 -0.0750 0.0235 0.7758 12.500 1.5639 0.02894 0.02215 -0.0734 0.0226 0.7772 12.750 1.5776 0.02979 0.02312 -0.0717 0.0214 0.7786 13.000 1.5901 0.03075 0.02417 -0.0699 0.0199 0.7802 13.250 1.6015 0.03182 0.02532 -0.0681 0.0187 0.7819 13.500 1.6123 0.03295 0.02654 -0.0663 0.0177 0.7836 13.750 1.6219 0.03419 0.02785 -0.0644 0.0166 0.7852 14.000 1.6302 0.03557 0.02931 -0.0626 0.0158 0.7869 14.250 1.6383 0.03697 0.03082 -0.0608 0.0151 0.7885 14.500 1.6451 0.03849 0.03245 -0.0590 0.0145 0.7902 14.750 1.6506 0.04017 0.03422 -0.0572 0.0139 0.7919 15.000 1.6544 0.04201 0.03618 -0.0555 0.0134 0.7935 15.250 1.6563 0.04409 0.03838 -0.0538 0.0129 0.7950 15.500 1.6573 0.04629 0.04071 -0.0522 0.0125 0.7965 15.750 1.6584 0.04855 0.04312 -0.0508 0.0121 0.7981 16.000 1.6576 0.05110 0.04580 -0.0496 0.0118 0.7997 16.250 1.6548 0.05395 0.04881 -0.0487 0.0115 0.8013 16.500 1.6501 0.05715 0.05214 -0.0480 0.0112 0.8030 16.750 1.6431 0.06082 0.05597 -0.0476 0.0109 0.8047 17.000 1.6341 0.06502 0.06031 -0.0479 0.0107 0.8064 17.250 1.6222 0.06990 0.06536 -0.0487 0.0105 0.8078 17.500 1.6063 0.07573 0.07137 -0.0504 0.0104 0.8090 17.750 1.5868 0.08266 0.07850 -0.0532 0.0103 0.8101 18.000 1.5610 0.09127 0.08733 -0.0574 0.0103 0.8110 18.250 1.5258 0.10226 0.09857 -0.0634 0.0104 0.8116 18.500 1.4727 0.11761 0.11424 -0.0723 0.0106 0.8116 18.750 1.3842 0.14112 0.13811 -0.0861 0.0113 0.8104