XFOIL Version 6.96 Calculated polar for: EPPLER 541 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 ------ -------- --------- --------- -------- -------- -------- -8.250 -0.4110 0.01703 0.01105 -0.0868 0.7962 0.0049 -8.000 -0.3900 0.01639 0.01034 -0.0860 0.7935 0.0049 -7.750 -0.3714 0.01563 0.00951 -0.0848 0.7908 0.0049 -7.500 -0.3520 0.01517 0.00898 -0.0837 0.7882 0.0048 -7.250 -0.3348 0.01457 0.00829 -0.0823 0.7855 0.0048 -7.000 -0.3199 0.01389 0.00756 -0.0804 0.7832 0.0050 -6.750 -0.3018 0.01345 0.00709 -0.0791 0.7807 0.0051 -6.500 -0.2846 0.01298 0.00656 -0.0776 0.7782 0.0052 -6.250 -0.2666 0.01257 0.00612 -0.0762 0.7759 0.0056 -6.000 -0.2475 0.01225 0.00575 -0.0750 0.7737 0.0058 -5.750 -0.2282 0.01195 0.00540 -0.0738 0.7714 0.0064 -5.500 -0.2119 0.01152 0.00495 -0.0720 0.7696 0.0097 -5.250 -0.1976 0.01105 0.00457 -0.0699 0.7675 0.0257 -5.000 -0.1846 0.01060 0.00425 -0.0676 0.7652 0.0536 -4.750 -0.1731 0.01018 0.00396 -0.0650 0.7629 0.0860 -4.500 -0.1657 0.00984 0.00375 -0.0616 0.7607 0.1211 -4.250 -0.1574 0.00940 0.00351 -0.0583 0.7586 0.1806 -4.000 -0.1512 0.00876 0.00323 -0.0549 0.7565 0.2722 -3.750 -0.1532 0.00761 0.00274 -0.0501 0.7544 0.4382 -3.500 -0.1533 0.00615 0.00230 -0.0456 0.7521 0.6928 -3.250 -0.1248 0.00633 0.00250 -0.0458 0.7504 0.7283 -3.000 -0.0956 0.00652 0.00265 -0.0462 0.7489 0.7402 -2.750 -0.0662 0.00673 0.00282 -0.0466 0.7473 0.7480 -2.500 -0.0368 0.00694 0.00300 -0.0470 0.7458 0.7539 -2.250 -0.0068 0.00734 0.00339 -0.0473 0.7441 0.7610 -2.000 0.0228 0.00778 0.00385 -0.0475 0.7426 0.7678 -1.750 0.0528 0.00832 0.00443 -0.0475 0.7412 0.7731 -1.500 0.0816 0.00841 0.00449 -0.0479 0.7396 0.7758 -1.250 0.1103 0.00836 0.00441 -0.0485 0.7378 0.7772 -1.000 0.1392 0.00833 0.00433 -0.0491 0.7361 0.7782 -0.750 0.1678 0.00824 0.00421 -0.0497 0.7343 0.7791 -0.500 0.1966 0.00817 0.00412 -0.0502 0.7326 0.7798 -0.250 0.2255 0.00815 0.00406 -0.0507 0.7305 0.7804 0.000 0.2542 0.00813 0.00403 -0.0512 0.7281 0.7809 0.250 0.2821 0.00808 0.00399 -0.0515 0.7254 0.7816 0.500 0.3103 0.00803 0.00394 -0.0519 0.7223 0.7821 0.750 0.3389 0.00798 0.00387 -0.0524 0.7192 0.7827 1.000 0.3678 0.00796 0.00382 -0.0529 0.7164 0.7832 1.250 0.3963 0.00794 0.00380 -0.0534 0.7136 0.7838 1.500 0.4241 0.00790 0.00378 -0.0537 0.7105 0.7845 1.750 0.4523 0.00786 0.00375 -0.0541 0.7071 0.7852 2.000 0.4807 0.00782 0.00370 -0.0545 0.7037 0.7858 2.250 0.5094 0.00782 0.00368 -0.0550 0.7002 0.7864 2.500 0.5368 0.00776 0.00366 -0.0553 0.6965 0.7871 2.750 0.5646 0.00771 0.00363 -0.0556 0.6923 0.7877 3.000 0.5927 0.00769 0.00359 -0.0560 0.6880 0.7884 3.250 0.6201 0.00766 0.00359 -0.0562 0.6832 0.7890 3.500 0.6473 0.00762 0.00357 -0.0564 0.6778 0.7897 3.750 0.6748 0.00762 0.00356 -0.0567 0.6724 0.7904 4.000 0.7017 0.00759 0.00359 -0.0568 0.6656 0.7911 4.250 0.7282 0.00759 0.00358 -0.0568 0.6581 0.7916 4.500 0.7545 0.00758 0.00359 -0.0568 0.6481 0.7921 4.750 0.7797 0.00760 0.00361 -0.0566 0.6350 0.7925 5.000 0.8027 0.00763 0.00361 -0.0559 0.6169 0.7932 5.250 0.8228 0.00773 0.00365 -0.0546 0.5892 0.7939 5.500 0.8360 0.00804 0.00379 -0.0520 0.5453 0.7946 5.750 0.8460 0.00846 0.00402 -0.0487 0.5003 0.7953 6.000 0.8544 0.00890 0.00430 -0.0452 0.4597 0.7961 6.250 0.8557 0.00936 0.00459 -0.0402 0.4169 0.7970 6.500 0.8566 0.00996 0.00498 -0.0354 0.3714 0.7980 6.750 0.8620 0.01055 0.00542 -0.0316 0.3343 0.7991 7.000 0.8680 0.01116 0.00588 -0.0280 0.2981 0.8000 7.250 0.8744 0.01179 0.00636 -0.0247 0.2644 0.8009 7.500 0.8820 0.01244 0.00687 -0.0217 0.2341 0.8018 7.750 0.8917 0.01306 0.00738 -0.0192 0.2080 0.8027 8.000 0.9017 0.01370 0.00792 -0.0168 0.1831 0.8035 8.250 0.9117 0.01438 0.00850 -0.0145 0.1596 0.8043 8.500 0.9221 0.01509 0.00910 -0.0124 0.1381 0.8051 8.750 0.9333 0.01579 0.00973 -0.0104 0.1177 0.8057 9.000 0.9431 0.01659 0.01042 -0.0084 0.0971 0.8063 9.250 0.9541 0.01736 0.01109 -0.0065 0.0786 0.8069 9.500 0.9660 0.01805 0.01174 -0.0049 0.0652 0.8079 9.750 0.9770 0.01884 0.01246 -0.0031 0.0517 0.8089 10.000 0.9885 0.01964 0.01320 -0.0015 0.0402 0.8098 10.250 1.0003 0.02044 0.01397 0.0000 0.0312 0.8106 10.500 1.0132 0.02121 0.01473 0.0014 0.0251 0.8114 10.750 1.0257 0.02202 0.01552 0.0027 0.0210 0.8122 11.000 1.0396 0.02277 0.01632 0.0038 0.0181 0.8130 11.250 1.0541 0.02349 0.01708 0.0048 0.0168 0.8138 11.500 1.0667 0.02435 0.01793 0.0060 0.0143 0.8146 11.750 1.0789 0.02526 0.01888 0.0072 0.0123 0.8154 12.000 1.0936 0.02600 0.01967 0.0080 0.0111 0.8162 12.250 1.1045 0.02703 0.02069 0.0092 0.0089 0.8171 12.500 1.1159 0.02805 0.02175 0.0103 0.0069 0.8179 12.750 1.1240 0.02933 0.02304 0.0116 0.0046 0.8186 13.000 1.1344 0.03047 0.02423 0.0127 0.0041 0.8194 13.250 1.1404 0.03199 0.02581 0.0141 0.0032 0.8200 13.500 1.1459 0.03360 0.02752 0.0154 0.0030 0.8206 13.750 1.1542 0.03498 0.02898 0.0164 0.0029 0.8216 14.000 1.1632 0.03633 0.03041 0.0173 0.0026 0.8226 14.250 1.1698 0.03791 0.03210 0.0182 0.0025 0.8237 14.500 1.1759 0.03961 0.03388 0.0191 0.0024 0.8247 14.750 1.1817 0.04136 0.03572 0.0199 0.0023 0.8256 15.000 1.1853 0.04338 0.03784 0.0207 0.0023 0.8266 15.250 1.1887 0.04548 0.04004 0.0214 0.0022 0.8275 15.500 1.1918 0.04766 0.04231 0.0219 0.0021 0.8284 15.750 1.1932 0.05012 0.04487 0.0223 0.0020 0.8293 16.000 1.1935 0.05276 0.04762 0.0226 0.0020 0.8302 16.250 1.1932 0.05557 0.05054 0.0228 0.0020 0.8310 16.500 1.1911 0.05869 0.05378 0.0227 0.0019 0.8319 16.750 1.1868 0.06221 0.05742 0.0224 0.0019 0.8326 17.000 1.1787 0.06635 0.06169 0.0219 0.0018 0.8333 17.250 1.1756 0.07002 0.06547 0.0210 0.0018 0.8340 17.500 1.1617 0.07535 0.07096 0.0198 0.0018 0.8345 17.750 1.1521 0.08029 0.07604 0.0182 0.0018 0.8353 18.000 1.1442 0.08514 0.08103 0.0164 0.0017 0.8362 18.250 1.1335 0.09063 0.08666 0.0141 0.0018 0.8370 18.500 1.1268 0.09565 0.09180 0.0118 0.0017 0.8378 18.750 1.1144 0.10179 0.09808 0.0090 0.0017 0.8384 19.000 1.1018 0.10812 0.10456 0.0058 0.0017 0.8390