XFOIL Version 6.96 Calculated polar for: davissm 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 ------ -------- --------- --------- -------- -------- -------- -10.000 -0.3270 0.12122 0.11883 -0.0328 1.0000 0.0103 -9.750 -0.3233 0.11841 0.11604 -0.0334 1.0000 0.0104 -9.500 -0.3206 0.11571 0.11337 -0.0337 1.0000 0.0104 -9.250 -0.3117 0.11229 0.10996 -0.0361 0.9987 0.0104 -9.000 -0.3019 0.10876 0.10643 -0.0385 0.9863 0.0105 -8.500 -0.2753 0.10123 0.09889 -0.0461 0.9739 0.0105 -8.250 -0.2609 0.09721 0.09486 -0.0484 0.9710 0.0108 -8.000 -0.2427 0.09409 0.09174 -0.0520 0.9682 0.0113 -7.750 -0.2234 0.09051 0.08814 -0.0566 0.9644 0.0118 -7.500 -0.2041 0.08677 0.08438 -0.0616 0.9586 0.0120 -7.250 -0.1814 0.08285 0.08044 -0.0675 0.9534 0.0122 -7.000 -0.1570 0.07693 0.07447 -0.0765 0.9444 0.0104 -6.500 -0.1168 0.07011 0.06757 -0.0851 0.9297 0.0100 -6.250 -0.0932 0.06620 0.06361 -0.0907 0.9227 0.0100 -6.000 -0.0673 0.06164 0.05899 -0.0975 0.9151 0.0102 -5.750 -0.0344 0.05623 0.05350 -0.1064 0.9088 0.0106 -5.500 -0.0097 0.05361 0.05084 -0.1101 0.9024 0.0109 -5.250 0.0162 0.05171 0.04889 -0.1132 0.8967 0.0117 -5.000 0.0482 0.04845 0.04556 -0.1187 0.8911 0.0127 -4.750 0.0855 0.04408 0.04109 -0.1258 0.8854 0.0127 -4.500 0.1273 0.03925 0.03609 -0.1336 0.8807 0.0128 -4.250 0.1779 0.03267 0.02925 -0.1433 0.8757 0.0137 -4.000 0.2268 0.02606 0.02226 -0.1512 0.8710 0.0148 -3.750 0.2559 0.02514 0.02124 -0.1525 0.8659 0.0156 -3.500 0.2937 0.02143 0.01720 -0.1559 0.8605 0.0165 -3.250 0.3355 0.01533 0.01024 -0.1597 0.8559 0.0183 -3.000 0.3662 0.01368 0.00816 -0.1605 0.8508 0.0194 -2.750 0.3956 0.01237 0.00657 -0.1611 0.8446 0.0205 -2.500 0.4240 0.01191 0.00597 -0.1613 0.8386 0.0213 -2.250 0.4523 0.01145 0.00540 -0.1615 0.8319 0.0222 -2.000 0.4806 0.01099 0.00480 -0.1615 0.8249 0.0232 -1.750 0.5087 0.01058 0.00428 -0.1616 0.8181 0.0243 -1.500 0.5367 0.01036 0.00397 -0.1616 0.8109 0.0256 -1.250 0.5647 0.01017 0.00372 -0.1616 0.8038 0.0264 -1.000 0.5927 0.00965 0.00312 -0.1617 0.7963 0.0282 -0.750 0.6206 0.00947 0.00292 -0.1617 0.7880 0.0298 -0.500 0.6482 0.00934 0.00275 -0.1617 0.7793 0.0315 -0.250 0.6759 0.00925 0.00263 -0.1616 0.7698 0.0339 0.000 0.7035 0.00920 0.00254 -0.1616 0.7605 0.0359 0.250 0.7312 0.00907 0.00237 -0.1615 0.7512 0.0389 0.500 0.7587 0.00902 0.00230 -0.1615 0.7407 0.0426 0.750 0.7861 0.00901 0.00226 -0.1614 0.7300 0.0472 1.000 0.8134 0.00900 0.00225 -0.1612 0.7185 0.0579 1.250 0.8405 0.00898 0.00227 -0.1611 0.7064 0.0839 1.500 0.8675 0.00883 0.00237 -0.1611 0.6937 0.2197 1.750 0.8938 0.00863 0.00253 -0.1610 0.6762 0.4174 2.250 0.9444 0.00795 0.00266 -0.1601 0.6255 1.0000 2.500 0.9702 0.00817 0.00277 -0.1597 0.6027 1.0000 2.750 0.9955 0.00844 0.00290 -0.1592 0.5760 1.0000 3.000 1.0202 0.00875 0.00308 -0.1586 0.5449 1.0000 3.250 1.0450 0.00907 0.00326 -0.1580 0.5154 1.0000 3.500 1.0697 0.00940 0.00346 -0.1574 0.4863 1.0000 3.750 1.0928 0.00989 0.00373 -0.1566 0.4412 1.0000 4.000 1.1149 0.01049 0.00406 -0.1556 0.3870 1.0000 4.250 1.1354 0.01128 0.00450 -0.1545 0.3186 1.0000 4.500 1.1528 0.01243 0.00511 -0.1528 0.2189 1.0000 4.750 1.1654 0.01415 0.00609 -0.1504 0.0778 1.0000 5.000 1.1891 0.01455 0.00647 -0.1497 0.0659 1.0000 5.250 1.2128 0.01496 0.00685 -0.1491 0.0567 1.0000 5.500 1.2361 0.01537 0.00725 -0.1483 0.0482 1.0000 5.750 1.2597 0.01574 0.00762 -0.1476 0.0413 1.0000 6.000 1.2825 0.01618 0.00803 -0.1468 0.0345 1.0000 6.250 1.3051 0.01660 0.00846 -0.1460 0.0292 1.0000 6.500 1.3271 0.01708 0.00896 -0.1450 0.0248 1.0000 6.750 1.3487 0.01757 0.00946 -0.1440 0.0215 1.0000 7.000 1.3688 0.01817 0.01007 -0.1427 0.0183 1.0000 7.250 1.3896 0.01866 0.01063 -0.1415 0.0167 1.0000 7.500 1.4093 0.01923 0.01124 -0.1401 0.0153 1.0000 7.750 1.4275 0.01988 0.01195 -0.1385 0.0140 1.0000 8.000 1.4422 0.02079 0.01293 -0.1361 0.0128 1.0000 8.250 1.4590 0.02146 0.01368 -0.1343 0.0123 1.0000 8.500 1.4744 0.02219 0.01450 -0.1321 0.0118 1.0000 8.750 1.4891 0.02293 0.01532 -0.1299 0.0111 1.0000 9.000 1.5027 0.02367 0.01613 -0.1275 0.0105 1.0000 9.250 1.5140 0.02444 0.01698 -0.1247 0.0099 1.0000 9.500 1.5227 0.02542 0.01804 -0.1216 0.0095 1.0000 9.750 1.5285 0.02667 0.01937 -0.1181 0.0091 1.0000 10.000 1.5325 0.02815 0.02097 -0.1144 0.0087 1.0000 10.250 1.5415 0.02931 0.02224 -0.1117 0.0085 1.0000 10.500 1.5498 0.03057 0.02363 -0.1091 0.0083 1.0000 10.750 1.5578 0.03191 0.02510 -0.1066 0.0080 1.0000 11.000 1.5659 0.03327 0.02657 -0.1042 0.0076 1.0000 11.250 1.5749 0.03457 0.02799 -0.1020 0.0073 1.0000 11.500 1.5834 0.03593 0.02945 -0.1000 0.0069 1.0000 11.750 1.5905 0.03746 0.03108 -0.0978 0.0067 1.0000 12.000 1.5964 0.03913 0.03286 -0.0957 0.0065 1.0000 12.250 1.6012 0.04096 0.03480 -0.0936 0.0063 1.0000 12.500 1.6032 0.04313 0.03710 -0.0914 0.0061 1.0000 12.750 1.6008 0.04585 0.03997 -0.0889 0.0059 1.0000 13.000 1.5998 0.04851 0.04281 -0.0867 0.0058 1.0000 13.250 1.6011 0.05096 0.04543 -0.0849 0.0057 1.0000 13.500 1.6006 0.05365 0.04831 -0.0832 0.0056 1.0000 13.750 1.5988 0.05656 0.05143 -0.0816 0.0055 1.0000 14.000 1.5954 0.05976 0.05483 -0.0802 0.0053 1.0000 14.250 1.5897 0.06334 0.05862 -0.0789 0.0052 1.0000 14.500 1.5826 0.06722 0.06270 -0.0780 0.0051 1.0000 14.750 1.5734 0.07155 0.06725 -0.0774 0.0051 1.0000 15.000 1.5634 0.07618 0.07209 -0.0772 0.0050 1.0000 15.250 1.5517 0.08126 0.07738 -0.0774 0.0049 1.0000 15.500 1.5382 0.08684 0.08317 -0.0782 0.0048 1.0000 15.750 1.5238 0.09285 0.08938 -0.0795 0.0048 1.0000 16.000 1.5068 0.09965 0.09639 -0.0816 0.0047 1.0000 16.250 1.4894 0.10684 0.10380 -0.0843 0.0047 1.0000 16.500 1.4699 0.11482 0.11198 -0.0877 0.0047 1.0000 16.750 1.4465 0.12415 0.12152 -0.0924 0.0047 1.0000 17.000 1.4239 0.13395 0.13152 -0.0978 0.0047 1.0000 17.250 1.3970 0.14565 0.14343 -0.1049 0.0048 1.0000 17.500 1.3655 0.15986 0.15783 -0.1140 0.0049 1.0000