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 = 0.300 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- 0.000 0.6327 0.01064 0.00450 -0.1440 0.9108 0.2285 1.500 0.7860 0.00843 0.00361 -0.1381 0.8339 1.0000 2.000 0.8404 0.00852 0.00355 -0.1372 0.8050 1.0000 2.500 0.8944 0.00869 0.00362 -0.1362 0.7709 1.0000 3.000 0.9477 0.00895 0.00372 -0.1351 0.7289 1.0000 3.500 0.9996 0.00935 0.00390 -0.1338 0.6738 1.0000 4.000 1.0493 0.00997 0.00423 -0.1322 0.5943 1.0000 4.500 1.0927 0.01125 0.00481 -0.1297 0.4540 1.0000 5.000 1.1318 0.01324 0.00590 -0.1270 0.2891 1.0000 5.500 1.1767 0.01461 0.00689 -0.1254 0.2220 1.0000 6.000 1.2234 0.01568 0.00776 -0.1240 0.1765 1.0000 6.500 1.2704 0.01665 0.00864 -0.1226 0.1474 1.0000 7.000 1.3161 0.01768 0.00952 -0.1211 0.1138 1.0000 7.500 1.3606 0.01877 0.01054 -0.1194 0.0892 1.0000 8.000 1.4033 0.01997 0.01170 -0.1173 0.0666 1.0000 8.500 1.4438 0.02129 0.01300 -0.1150 0.0485 1.0000 9.000 1.4826 0.02265 0.01445 -0.1123 0.0374 1.0000 9.500 1.5177 0.02422 0.01608 -0.1090 0.0254 1.0000 10.000 1.5480 0.02605 0.01798 -0.1051 0.0152 1.0000 10.500 1.5700 0.02833 0.02040 -0.0998 0.0065 1.0000 11.000 1.5860 0.03089 0.02320 -0.0937 0.0045 1.0000 11.500 1.6003 0.03374 0.02638 -0.0880 0.0039 1.0000 12.000 1.6096 0.03715 0.03014 -0.0825 0.0036 1.0000 12.500 1.6116 0.04139 0.03478 -0.0771 0.0035 1.0000 13.000 1.6055 0.04671 0.04050 -0.0723 0.0034 1.0000 13.500 1.5925 0.05330 0.04749 -0.0688 0.0033 1.0000 14.000 1.5732 0.06145 0.05604 -0.0671 0.0033 1.0000 14.500 1.5468 0.07169 0.06669 -0.0679 0.0033 1.0000 15.000 1.5146 0.08450 0.07989 -0.0717 0.0033 1.0000 15.500 1.4762 0.10034 0.09612 -0.0788 0.0033 1.0000 16.000 1.4370 0.11820 0.11438 -0.0881 0.0034 1.0000 16.500 1.3988 0.13686 0.13336 -0.0981 0.0035 1.0000 17.000 1.3627 0.15544 0.15219 -0.1087 0.0036 1.0000 17.500 1.3350 0.17274 0.16971 -0.1191 0.0037 1.0000 18.000 1.3165 0.18847 0.18561 -0.1290 0.0038 1.0000 18.500 1.3035 0.20359 0.20090 -0.1387 0.0039 1.0000 19.000 1.2874 0.22166 0.21916 -0.1504 0.0041 1.0000 20.000 1.2594 0.27264 0.27008 -0.1787 0.0068 1.0000 21.000 0.8794 0.26325 0.26094 -0.1236 0.0162 1.0000 21.500 0.8821 0.27100 0.26871 -0.1261 0.0156 1.0000 22.000 0.8856 0.27826 0.27599 -0.1284 0.0150 1.0000 22.500 0.8903 0.28470 0.28245 -0.1302 0.0144 1.0000 23.000 0.8942 0.29203 0.28980 -0.1321 0.0142 1.0000 23.500 0.8947 0.30126 0.29904 -0.1355 0.0137 1.0000 24.000 0.8980 0.30892 0.30672 -0.1379 0.0128 1.0000 24.500 0.9016 0.31602 0.31385 -0.1401 0.0121 1.0000 25.000 0.9059 0.32241 0.32027 -0.1418 0.0117 1.0000 25.500 0.9082 0.33050 0.32838 -0.1443 0.0115 1.0000 26.000 0.9103 0.33909 0.33698 -0.1471 0.0111 1.0000 26.500 0.9132 0.34678 0.34470 -0.1494 0.0104 1.0000 27.000 0.9159 0.35410 0.35205 -0.1516 0.0099 1.0000 27.500 0.9185 0.36108 0.35907 -0.1538 0.0094 1.0000 28.500 0.9228 0.37602 0.37407 -0.1581 0.0091 1.0000 29.000 0.9244 0.38427 0.38234 -0.1607 0.0089 1.0000 29.500 0.9262 0.39210 0.39021 -0.1630 0.0085 1.0000 30.000 0.9278 0.39965 0.39779 -0.1653 0.0080 1.0000 30.500 0.9291 0.40709 0.40526 -0.1675 0.0076 1.0000 31.000 0.9301 0.41426 0.41247 -0.1697 0.0073 1.0000 31.500 0.9307 0.42104 0.41928 -0.1718 0.0070 1.0000 32.000 0.9312 0.42939 0.42766 -0.1741 0.0068 1.0000 32.500 0.9320 0.43781 0.43610 -0.1763 0.0063 1.0000 33.000 0.9322 0.44544 0.44376 -0.1785 0.0057 1.0000 33.500 0.9321 0.45267 0.45103 -0.1807 0.0053 1.0000 34.000 0.9313 0.45939 0.45779 -0.1828 0.0050 1.0000 35.000 0.9301 0.47544 0.47389 -0.1871 0.0049 1.0000 35.500 0.9295 0.48330 0.48178 -0.1892 0.0045 1.0000 36.000 0.9284 0.49062 0.48913 -0.1913 0.0039 1.0000 36.500 0.9268 0.49747 0.49601 -0.1935 0.0036 1.0000 37.000 0.9242 0.50368 0.50227 -0.1955 0.0034 1.0000 37.500 0.9226 0.51190 0.51050 -0.1976 0.0033 1.0000 38.000 0.9210 0.51968 0.51831 -0.1996 0.0032 1.0000 38.500 0.9189 0.52687 0.52554 -0.2016 0.0029 1.0000 39.000 0.9162 0.53360 0.53229 -0.2036 0.0027 1.0000 39.500 0.9132 0.54014 0.53887 -0.2057 0.0025 1.0000 40.000 0.9099 0.54634 0.54511 -0.2077 0.0023 1.0000 40.500 0.9063 0.55228 0.55108 -0.2097 0.0022 1.0000 41.000 0.9019 0.55778 0.55662 -0.2118 0.0021 1.0000 42.500 0.8896 0.57608 0.57501 -0.2176 0.0020 1.0000 43.000 0.8854 0.58187 0.58082 -0.2194 0.0020 1.0000 43.500 0.8810 0.58758 0.58657 -0.2213 0.0019 1.0000 44.000 0.8761 0.59286 0.59188 -0.2231 0.0018 1.0000 44.500 0.8709 0.59793 0.59698 -0.2249 0.0016 1.0000 45.000 0.8654 0.60272 0.60181 -0.2268 0.0014 1.0000 45.500 0.8596 0.60716 0.60628 -0.2286 0.0013 1.0000 46.000 0.8535 0.61120 0.61035 -0.2304 0.0012 1.0000 46.500 0.8469 0.61484 0.61403 -0.2323 0.0011 1.0000 47.000 0.8395 0.61829 0.61752 -0.2341 0.0011 1.0000 49.000 0.8130 0.63278 0.63211 -0.2408 0.0011 1.0000 49.500 0.8058 0.63560 0.63497 -0.2425 0.0011 1.0000 50.000 0.7983 0.63801 0.63740 -0.2441 0.0011 1.0000 50.500 0.7907 0.64027 0.63969 -0.2457 0.0010 1.0000 51.000 0.7828 0.64224 0.64170 -0.2472 0.0010 1.0000 51.500 0.7747 0.64384 0.64332 -0.2488 0.0010 1.0000 52.000 0.7665 0.64523 0.64474 -0.2503 0.0010 1.0000 52.500 0.7580 0.64631 0.64586 -0.2518 0.0010 1.0000 53.000 0.7495 0.64721 0.64679 -0.2533 0.0009 1.0000 53.500 0.7407 0.64789 0.64749 -0.2548 0.0009 1.0000 54.000 0.7318 0.64829 0.64793 -0.2562 0.0008 1.0000 54.500 0.7228 0.64850 0.64816 -0.2576 0.0008 1.0000 55.000 0.7136 0.64837 0.64806 -0.2590 0.0007 1.0000 55.500 0.7042 0.64799 0.64770 -0.2604 0.0007 1.0000 56.000 0.6947 0.64740 0.64714 -0.2618 0.0006 1.0000 56.500 0.6850 0.64632 0.64609 -0.2631 0.0006 1.0000 57.000 0.6752 0.64515 0.64494 -0.2644 0.0005 1.0000 57.500 0.6652 0.64354 0.64336 -0.2657 0.0005 1.0000 58.000 0.6551 0.64169 0.64153 -0.2670 0.0005 1.0000 58.500 0.6449 0.63960 0.63947 -0.2682 0.0005 1.0000 59.000 0.6344 0.63729 0.63719 -0.2695 0.0004 1.0000 59.500 0.6236 0.63461 0.63453 -0.2708 0.0004 1.0000