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 = 0.200 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -12.250 -0.4318 0.10852 0.10496 -0.0483 1.0000 0.0792 -12.000 -0.5708 0.07027 0.06645 -0.0665 1.0000 0.0473 -11.750 -0.5948 0.06452 0.06066 -0.0672 1.0000 0.0467 -11.500 -0.6248 0.05910 0.05517 -0.0672 1.0000 0.0461 -11.250 -0.6574 0.05443 0.05041 -0.0660 1.0000 0.0454 -11.000 -0.7686 0.06273 0.05836 -0.0630 1.0000 0.0467 -10.750 -0.7972 0.06095 0.05656 -0.0581 1.0000 0.0463 -10.500 -0.8786 0.05361 0.04838 -0.0513 1.0000 0.0401 -10.250 -0.8830 0.04995 0.04459 -0.0491 1.0000 0.0397 -10.000 -0.8859 0.04662 0.04104 -0.0471 1.0000 0.0393 -9.750 -0.8846 0.04335 0.03748 -0.0454 1.0000 0.0391 -9.500 -0.8787 0.04023 0.03403 -0.0441 1.0000 0.0389 -9.250 -0.8681 0.03760 0.03104 -0.0430 1.0000 0.0394 -9.000 -0.8537 0.03551 0.02857 -0.0422 1.0000 0.0400 -8.750 -0.8366 0.03362 0.02634 -0.0416 1.0000 0.0405 -8.500 -0.8181 0.03088 0.02341 -0.0409 1.0000 0.0411 -8.250 -0.7979 0.02921 0.02167 -0.0403 1.0000 0.0419 -8.000 -0.7771 0.02799 0.02038 -0.0396 1.0000 0.0430 -7.750 -0.7556 0.02690 0.01919 -0.0390 1.0000 0.0442 -7.500 -0.7337 0.02593 0.01812 -0.0385 1.0000 0.0459 -7.250 -0.7109 0.02519 0.01722 -0.0380 1.0000 0.0480 -7.000 -0.6891 0.02391 0.01598 -0.0374 1.0000 0.0504 -6.750 -0.6623 0.02312 0.01521 -0.0379 0.9993 0.0533 -6.500 -0.6297 0.02241 0.01441 -0.0393 0.9977 0.0573 -6.250 -0.5965 0.02145 0.01357 -0.0413 0.9961 0.0638 -6.000 -0.5608 0.02064 0.01279 -0.0438 0.9948 0.0732 -5.750 -0.5261 0.01983 0.01203 -0.0462 0.9932 0.0856 -5.500 -0.4907 0.01909 0.01136 -0.0489 0.9917 0.1024 -5.250 -0.4526 0.01826 0.01069 -0.0523 0.9904 0.1295 -5.000 -0.3910 0.01544 0.00949 -0.0634 0.9927 0.4151 -4.750 -0.3537 0.01517 0.00972 -0.0659 0.9915 0.5355 -4.500 -0.3217 0.01542 0.01007 -0.0666 0.9890 0.5782 -4.250 -0.2882 0.01577 0.01040 -0.0677 0.9868 0.6052 -4.000 -0.2555 0.01627 0.01088 -0.0685 0.9849 0.6249 -3.750 -0.2311 0.01671 0.01130 -0.0676 0.9810 0.6407 -3.500 -0.2050 0.01733 0.01191 -0.0668 0.9777 0.6554 -3.250 -0.1770 0.01807 0.01262 -0.0663 0.9749 0.6692 -3.000 -0.1441 0.01877 0.01327 -0.0669 0.9728 0.6822 -2.750 -0.1307 0.01936 0.01390 -0.0633 0.9679 0.6866 -2.500 -0.1000 0.01973 0.01421 -0.0641 0.9648 0.6977 -2.250 -0.0767 0.02039 0.01489 -0.0622 0.9616 0.7020 -2.000 -0.0439 0.02082 0.01529 -0.0631 0.9596 0.7098 -1.750 -0.0207 0.02100 0.01545 -0.0624 0.9548 0.7154 -1.500 0.0052 0.02125 0.01570 -0.0618 0.9503 0.7192 -1.250 0.0431 0.02135 0.01575 -0.0643 0.9474 0.7267 -1.000 0.0788 0.02155 0.01595 -0.0657 0.9449 0.7312 -0.750 0.0963 0.02180 0.01622 -0.0635 0.9381 0.7354 -0.500 0.1369 0.02180 0.01618 -0.0669 0.9342 0.7443 -0.250 0.1713 0.02183 0.01624 -0.0676 0.9305 0.7468 0.000 0.1959 0.02192 0.01636 -0.0668 0.9237 0.7504 0.250 0.2326 0.02181 0.01626 -0.0685 0.9178 0.7558 0.500 0.2918 0.02118 0.01564 -0.0741 0.9135 0.7615 0.750 0.3405 0.02003 0.01453 -0.0760 0.8995 0.7643 1.000 0.3884 0.01899 0.01352 -0.0782 0.8879 0.7680 1.250 0.4409 0.01804 0.01259 -0.0821 0.8825 0.7727 1.500 0.4738 0.01758 0.01217 -0.0828 0.8720 0.7776 1.750 0.5109 0.01686 0.01150 -0.0833 0.8650 0.7806 2.000 0.5368 0.01651 0.01121 -0.0821 0.8523 0.7848 2.250 0.5706 0.01607 0.01081 -0.0830 0.8387 0.7899 2.500 0.6011 0.01560 0.01037 -0.0829 0.8211 0.7938 2.750 0.6247 0.01524 0.01005 -0.0811 0.7991 0.7973 3.000 0.6508 0.01494 0.00974 -0.0799 0.7647 0.8020 3.250 0.6838 0.01477 0.00925 -0.0804 0.6661 0.8076 3.500 0.6866 0.01579 0.00920 -0.0746 0.4792 0.8107 3.750 0.6893 0.01719 0.00974 -0.0700 0.3214 0.8148 4.000 0.7035 0.01841 0.01032 -0.0683 0.2178 0.8194 4.250 0.7268 0.01922 0.01083 -0.0682 0.1824 0.8231 4.500 0.7447 0.01967 0.01120 -0.0663 0.1668 0.8258 4.750 0.7655 0.02013 0.01163 -0.0651 0.1560 0.8292 5.000 0.7882 0.02082 0.01221 -0.0645 0.1474 0.8332 5.250 0.8181 0.02133 0.01275 -0.0654 0.1405 0.8372 5.500 0.8389 0.02178 0.01317 -0.0642 0.1349 0.8399 5.750 0.8618 0.02236 0.01376 -0.0634 0.1296 0.8427 6.000 0.8869 0.02277 0.01421 -0.0632 0.1245 0.8460 6.250 0.9144 0.02338 0.01478 -0.0636 0.1199 0.8494 6.500 0.9460 0.02436 0.01572 -0.0649 0.1159 0.8521 6.750 0.9693 0.02474 0.01623 -0.0641 0.1127 0.8544 7.000 0.9933 0.02524 0.01680 -0.0636 0.1093 0.8572 7.250 1.0193 0.02589 0.01744 -0.0636 0.1061 0.8602 7.500 1.0510 0.02738 0.01891 -0.0649 0.1024 0.8630 7.750 1.0789 0.02798 0.01970 -0.0653 0.0998 0.8656 8.000 1.1043 0.02870 0.02055 -0.0651 0.0967 0.8681 8.250 1.1273 0.02941 0.02137 -0.0644 0.0937 0.8708 8.500 1.1531 0.03044 0.02239 -0.0645 0.0906 0.8735 8.750 1.1791 0.03210 0.02422 -0.0647 0.0873 0.8760 9.000 1.2015 0.03279 0.02512 -0.0641 0.0839 0.8788 9.250 1.2249 0.03351 0.02595 -0.0639 0.0805 0.8816 9.500 1.2461 0.03436 0.02678 -0.0633 0.0777 0.8840 9.750 1.2663 0.03632 0.02895 -0.0626 0.0750 0.8863 10.000 1.2829 0.03740 0.03034 -0.0610 0.0727 0.8892 10.250 1.3014 0.03841 0.03153 -0.0600 0.0700 0.8921 10.500 1.3208 0.03910 0.03227 -0.0593 0.0676 0.8946 10.750 1.3430 0.04122 0.03434 -0.0596 0.0650 0.8966 11.000 1.3485 0.04217 0.03571 -0.0563 0.0632 0.8990 11.250 1.3574 0.04325 0.03704 -0.0539 0.0607 0.9016 11.500 1.3700 0.04370 0.03755 -0.0522 0.0585 0.9047 11.750 1.3879 0.04414 0.03787 -0.0515 0.0565 0.9077 12.000 1.3867 0.04631 0.04034 -0.0482 0.0547 0.9102 12.250 1.3799 0.04804 0.04244 -0.0440 0.0530 0.9128 12.500 1.3793 0.04962 0.04423 -0.0410 0.0513 0.9156 12.750 1.3837 0.05064 0.04534 -0.0390 0.0498 0.9185 13.000 1.3974 0.05112 0.04573 -0.0380 0.0483 0.9215 13.250 1.3956 0.05382 0.04857 -0.0361 0.0470 0.9241 13.500 1.3760 0.05720 0.05236 -0.0327 0.0461 0.9271 13.750 1.3555 0.06118 0.05672 -0.0303 0.0453 0.9302 14.000 1.3339 0.06573 0.06159 -0.0288 0.0445 0.9332 14.250 1.3124 0.07063 0.06677 -0.0284 0.0439 0.9360 14.500 1.2839 0.07697 0.07341 -0.0292 0.0436 0.9384 14.750 1.2302 0.08796 0.08479 -0.0333 0.0442 0.9397 15.000 1.1624 0.10443 0.10163 -0.0434 0.0457 0.9397