XFOIL Version 6.94 Calculated polar for: ARA-D 6% AIRFOIL 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 0.6268 0.00866 0.00297 -0.1398 0.8744 0.1949 0.500 0.6816 0.00834 0.00283 -0.1391 0.8481 0.2865 1.000 0.7295 0.00685 0.00271 -0.1371 0.8213 1.0000 1.500 0.7849 0.00700 0.00271 -0.1366 0.7924 1.0000 2.000 0.8397 0.00722 0.00273 -0.1360 0.7588 1.0000 2.500 0.8940 0.00751 0.00286 -0.1353 0.7178 1.0000 3.000 0.9472 0.00790 0.00304 -0.1345 0.6663 1.0000 3.500 0.9989 0.00848 0.00331 -0.1335 0.5955 1.0000 4.000 1.0468 0.00948 0.00379 -0.1319 0.4812 1.0000 4.500 1.0900 0.01119 0.00462 -0.1300 0.3121 1.0000 5.000 1.1352 0.01270 0.00549 -0.1285 0.2072 1.0000 5.500 1.1850 0.01351 0.00614 -0.1276 0.1719 1.0000 6.000 1.2336 0.01441 0.00684 -0.1265 0.1321 1.0000 6.500 1.2819 0.01527 0.00757 -0.1254 0.1040 1.0000 7.000 1.3285 0.01626 0.00843 -0.1240 0.0773 1.0000 7.500 1.3724 0.01747 0.00947 -0.1222 0.0484 1.0000 8.000 1.4161 0.01863 0.01059 -0.1202 0.0325 1.0000 8.500 1.4567 0.02001 0.01193 -0.1178 0.0176 1.0000 9.000 1.4956 0.02144 0.01340 -0.1151 0.0092 1.0000 9.500 1.5291 0.02329 0.01535 -0.1114 0.0027 1.0000 10.000 1.5619 0.02493 0.01721 -0.1077 0.0024 1.0000 10.500 1.5898 0.02677 0.01932 -0.1032 0.0022 1.0000 11.000 1.6088 0.02892 0.02176 -0.0973 0.0022 1.0000 11.500 1.6234 0.03155 0.02471 -0.0913 0.0021 1.0000 12.000 1.6329 0.03475 0.02824 -0.0854 0.0021 1.0000 12.500 1.6352 0.03874 0.03258 -0.0796 0.0021 1.0000 13.000 1.6310 0.04364 0.03782 -0.0745 0.0021 1.0000 13.500 1.6201 0.04973 0.04427 -0.0705 0.0021 1.0000 14.000 1.6029 0.05729 0.05219 -0.0682 0.0021 1.0000 14.500 1.5799 0.06668 0.06194 -0.0681 0.0021 1.0000 15.000 1.5514 0.07832 0.07395 -0.0708 0.0021 1.0000 15.500 1.5175 0.09261 0.08861 -0.0764 0.0021 1.0000 16.000 1.4784 0.10972 0.10608 -0.0847 0.0021 1.0000 16.500 1.4376 0.12843 0.12511 -0.0944 0.0022 1.0000 17.000 1.3986 0.14713 0.14406 -0.1046 0.0022 1.0000 17.500 1.3674 0.16451 0.16165 -0.1146 0.0022 1.0000 18.000 1.3457 0.18045 0.17777 -0.1245 0.0023 1.0000 18.500 1.3318 0.19490 0.19237 -0.1337 0.0023 1.0000 19.000 1.3227 0.20869 0.20631 -0.1427 0.0024 1.0000 19.500 1.3151 0.22294 0.22071 -0.1521 0.0025 1.0000 20.000 1.3017 0.24167 0.23963 -0.1643 0.0026 1.0000 20.500 0.8908 0.24664 0.24478 -0.1209 0.0042 1.0000 21.000 0.8907 0.25521 0.25335 -0.1235 0.0048 1.0000 21.500 0.8843 0.27017 0.26829 -0.1266 0.0108 1.0000 22.000 0.8870 0.27802 0.27616 -0.1291 0.0104 1.0000 22.500 0.8903 0.28545 0.28360 -0.1314 0.0099 1.0000 23.000 0.8940 0.29235 0.29052 -0.1336 0.0095 1.0000 23.500 0.8988 0.29843 0.29663 -0.1354 0.0092 1.0000 24.000 0.9017 0.30630 0.30451 -0.1376 0.0091 1.0000 24.500 0.9027 0.31582 0.31404 -0.1407 0.0088 1.0000 25.000 0.9058 0.32373 0.32196 -0.1431 0.0081 1.0000 25.500 0.9089 0.33109 0.32935 -0.1454 0.0076 1.0000 26.000 0.9120 0.33803 0.33631 -0.1476 0.0072 1.0000 26.500 0.9153 0.34442 0.34273 -0.1495 0.0070 1.0000 27.000 0.9179 0.35200 0.35033 -0.1516 0.0069 1.0000 27.500 0.9193 0.36061 0.35896 -0.1544 0.0068 1.0000 28.000 0.9217 0.36900 0.36737 -0.1568 0.0065 1.0000 28.500 0.9239 0.37673 0.37512 -0.1591 0.0061 1.0000 29.000 0.9258 0.38420 0.38262 -0.1614 0.0058 1.0000 29.500 0.9275 0.39151 0.38997 -0.1636 0.0055 1.0000 30.000 0.9289 0.39864 0.39712 -0.1658 0.0053 1.0000 30.500 0.9300 0.40548 0.40399 -0.1680 0.0051 1.0000 31.500 0.9314 0.42110 0.41966 -0.1725 0.0049 1.0000 32.000 0.9326 0.42977 0.42835 -0.1747 0.0044 1.0000 32.500 0.9330 0.43739 0.43600 -0.1769 0.0039 1.0000 33.000 0.9330 0.44451 0.44315 -0.1791 0.0036 1.0000 33.500 0.9324 0.45106 0.44973 -0.1813 0.0034 1.0000 34.500 0.9314 0.46724 0.46594 -0.1856 0.0033 1.0000 35.000 0.9315 0.47563 0.47436 -0.1877 0.0029 1.0000 35.500 0.9304 0.48294 0.48169 -0.1898 0.0026 1.0000 36.000 0.9291 0.48987 0.48866 -0.1919 0.0023 1.0000 36.500 0.9269 0.49607 0.49488 -0.1941 0.0021 1.0000 37.000 0.9247 0.50365 0.50249 -0.1961 0.0020 1.0000 37.500 0.9236 0.51209 0.51095 -0.1981 0.0020 1.0000 38.000 0.9219 0.51970 0.51858 -0.2001 0.0019 1.0000 38.500 0.9196 0.52680 0.52571 -0.2021 0.0017 1.0000 39.000 0.9169 0.53348 0.53241 -0.2041 0.0015 1.0000 39.500 0.9139 0.54001 0.53897 -0.2062 0.0014 1.0000 40.000 0.9106 0.54623 0.54521 -0.2082 0.0013 1.0000 40.500 0.9070 0.55223 0.55124 -0.2102 0.0012 1.0000 41.000 0.9030 0.55786 0.55691 -0.2122 0.0012 1.0000 41.500 0.8984 0.56317 0.56225 -0.2143 0.0011 1.0000 43.000 0.8851 0.58087 0.58002 -0.2200 0.0011 1.0000 43.500 0.8807 0.58677 0.58595 -0.2219 0.0011 1.0000 44.000 0.8761 0.59241 0.59161 -0.2236 0.0010 1.0000 44.500 0.8713 0.59793 0.59715 -0.2254 0.0010 1.0000 45.000 0.8660 0.60301 0.60226 -0.2272 0.0009 1.0000 45.500 0.8604 0.60770 0.60698 -0.2290 0.0008 1.0000 46.000 0.8544 0.61205 0.61135 -0.2307 0.0007 1.0000 46.500 0.8482 0.61611 0.61544 -0.2325 0.0006 1.0000 47.000 0.8418 0.61981 0.61916 -0.2343 0.0006 1.0000 47.500 0.8351 0.62331 0.62269 -0.2360 0.0005 1.0000 48.000 0.8282 0.62655 0.62596 -0.2378 0.0005 1.0000 48.500 0.8210 0.62930 0.62873 -0.2395 0.0005 1.0000 49.000 0.8135 0.63190 0.63136 -0.2413 0.0005 1.0000 49.500 0.8057 0.63414 0.63362 -0.2430 0.0004 1.0000 50.000 0.7973 0.63607 0.63558 -0.2447 0.0004 1.0000 52.000 0.7658 0.64415 0.64375 -0.2509 0.0004 1.0000 52.500 0.7577 0.64550 0.64513 -0.2523 0.0004 1.0000 53.000 0.7494 0.64662 0.64627 -0.2537 0.0004 1.0000 53.500 0.7408 0.64746 0.64713 -0.2552 0.0004 1.0000 54.000 0.7320 0.64798 0.64768 -0.2566 0.0003 1.0000 54.500 0.7230 0.64821 0.64793 -0.2580 0.0003 1.0000 55.000 0.7137 0.64805 0.64779 -0.2594 0.0003 1.0000 55.500 0.7043 0.64755 0.64732 -0.2608 0.0002 1.0000 56.000 0.6947 0.64677 0.64656 -0.2622 0.0002 1.0000 56.500 0.6847 0.64546 0.64526 -0.2635 0.0002 1.0000