XFOIL Version 6.94 Calculated polar for: E197 (13.49%) 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.080 Re = 0.450 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- 0.000 0.2933 0.00832 0.00253 -0.0612 0.6322 0.6904 0.500 0.3467 0.00823 0.00262 -0.0606 0.6240 0.7483 1.000 0.3985 0.00809 0.00272 -0.0594 0.6155 0.8226 1.500 0.4525 0.00807 0.00290 -0.0585 0.6072 0.9068 2.000 0.5259 0.00818 0.00305 -0.0619 0.5983 0.9605 2.500 0.6072 0.00835 0.00320 -0.0674 0.5891 0.9837 3.000 0.6923 0.00846 0.00326 -0.0739 0.5788 0.9982 3.500 0.7443 0.00855 0.00338 -0.0734 0.5668 1.0000 4.000 0.7910 0.00869 0.00352 -0.0717 0.5546 1.0000 4.500 0.8385 0.00885 0.00368 -0.0701 0.5417 1.0000 5.000 0.8862 0.00901 0.00385 -0.0685 0.5271 1.0000 5.500 0.9335 0.00918 0.00406 -0.0668 0.5098 1.0000 6.000 0.9810 0.00937 0.00435 -0.0652 0.4900 1.0000 6.500 1.0270 0.00966 0.00464 -0.0633 0.4635 1.0000 7.000 1.0705 0.01010 0.00505 -0.0611 0.4223 1.0000 7.500 1.1050 0.01104 0.00570 -0.0575 0.3489 1.0000 8.000 1.1278 0.01266 0.00685 -0.0524 0.2531 1.0000 8.500 1.1450 0.01447 0.00825 -0.0465 0.1740 1.0000 9.500 1.1663 0.01790 0.01124 -0.0333 0.0837 1.0000 10.000 1.1761 0.02002 0.01323 -0.0279 0.0547 1.0000 10.500 1.1772 0.02308 0.01613 -0.0226 0.0255 1.0000 11.000 1.1761 0.02688 0.01996 -0.0183 0.0151 1.0000 11.500 1.1886 0.03001 0.02327 -0.0158 0.0134 1.0000 12.000 1.1952 0.03386 0.02726 -0.0136 0.0119 1.0000 12.500 1.1921 0.03883 0.03241 -0.0114 0.0111 1.0000 13.000 1.1915 0.04383 0.03760 -0.0100 0.0106 1.0000 13.500 1.1970 0.04852 0.04248 -0.0091 0.0100 1.0000 14.000 1.1998 0.05372 0.04787 -0.0086 0.0096 1.0000 14.500 1.2027 0.05922 0.05357 -0.0085 0.0091 1.0000 15.000 1.2048 0.06503 0.05959 -0.0087 0.0089 1.0000 15.500 1.2063 0.07126 0.06601 -0.0095 0.0085 1.0000 16.000 1.2059 0.07794 0.07291 -0.0106 0.0084 1.0000 16.500 1.2028 0.08541 0.08061 -0.0123 0.0082 1.0000 17.000 1.1965 0.09368 0.08914 -0.0149 0.0080 1.0000 17.500 1.1851 0.10319 0.09892 -0.0183 0.0078 1.0000 18.000 1.1713 0.11378 0.10983 -0.0230 0.0079 1.0000 18.500 1.1519 0.12586 0.12221 -0.0291 0.0078 1.0000 19.000 1.1280 0.13972 0.13640 -0.0369 0.0079 1.0000 19.500 1.0968 0.15633 0.15337 -0.0470 0.0080 1.0000