XFOIL Version 6.94 Calculated polar for: AH 79-100 B 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 0.8988 0.01021 0.00453 -0.2128 0.7638 0.6858 0.500 0.9495 0.01025 0.00472 -0.2115 0.7514 0.7543 1.000 1.0031 0.01027 0.00476 -0.2107 0.7403 0.8159 1.500 1.0430 0.01001 0.00473 -0.2070 0.7275 1.0000 2.000 1.1024 0.01027 0.00485 -0.2079 0.7162 1.0000 2.500 1.1570 0.01046 0.00498 -0.2077 0.7021 1.0000 3.000 1.2106 0.01069 0.00520 -0.2073 0.6868 1.0000 3.500 1.2645 0.01094 0.00539 -0.2069 0.6714 1.0000 4.000 1.3176 0.01119 0.00562 -0.2063 0.6541 1.0000 4.500 1.3672 0.01145 0.00590 -0.2050 0.6339 1.0000 5.000 1.4143 0.01174 0.00623 -0.2031 0.6085 1.0000 5.500 1.4601 0.01211 0.00664 -0.2011 0.5810 1.0000 6.000 1.5037 0.01263 0.00715 -0.1986 0.5501 1.0000 6.500 1.5434 0.01328 0.00777 -0.1954 0.5132 1.0000 7.000 1.5745 0.01424 0.00858 -0.1907 0.4629 1.0000 7.500 1.5950 0.01555 0.00966 -0.1841 0.4010 1.0000 8.000 1.6057 0.01721 0.01105 -0.1761 0.3365 1.0000 8.500 1.6085 0.01957 0.01306 -0.1674 0.2596 1.0000 9.000 1.6006 0.02307 0.01606 -0.1582 0.1702 1.0000 9.500 1.5878 0.02759 0.02006 -0.1498 0.0881 1.0000 10.500 1.5789 0.03721 0.02949 -0.1380 0.0317 1.0000 12.000 1.5843 0.05317 0.04595 -0.1281 0.0208 1.0000 12.500 1.5819 0.05987 0.05286 -0.1260 0.0197 1.0000 13.000 1.5856 0.06622 0.05945 -0.1244 0.0187 1.0000 13.500 1.5920 0.07254 0.06591 -0.1233 0.0178 1.0000 14.000 1.6077 0.07805 0.07155 -0.1218 0.0170 1.0000 14.500 1.6221 0.08388 0.07777 -0.1209 0.0162 1.0000 15.000 1.6312 0.09009 0.08419 -0.1210 0.0148 1.0000 15.500 1.6368 0.09735 0.09182 -0.1212 0.0138 1.0000 16.000 1.6316 0.10596 0.10087 -0.1229 0.0128 1.0000 16.500 1.6388 0.11247 0.10746 -0.1242 0.0118 1.0000 18.000 1.5701 0.15062 0.14726 -0.1420 0.0108 1.0000 18.500 1.5413 0.16597 0.16307 -0.1518 0.0107 1.0000 19.000 1.5081 0.18362 0.18115 -0.1642 0.0108 1.0000 19.500 1.4749 0.20297 0.20084 -0.1786 0.0111 1.0000 20.000 1.4439 0.22379 0.22187 -0.1940 0.0115 1.0000 22.000 1.1176 0.36530 0.36390 -0.2231 0.0176 1.0000 22.500 1.1257 0.37467 0.37329 -0.2246 0.0171 1.0000 23.000 1.1232 0.39171 0.39032 -0.2303 0.0154 1.0000 23.500 1.1280 0.40210 0.40075 -0.2328 0.0146 1.0000 24.000 1.1310 0.41503 0.41369 -0.2358 0.0142 1.0000 24.500 1.1333 0.42940 0.42806 -0.2395 0.0127 1.0000 25.000 1.1367 0.44072 0.43942 -0.2423 0.0121 1.0000 25.500 1.1393 0.45449 0.45320 -0.2454 0.0110 1.0000 26.000 1.1421 0.46704 0.46578 -0.2482 0.0101 1.0000 26.500 1.1451 0.47771 0.47648 -0.2504 0.0094 1.0000 27.500 1.1489 0.50662 0.50542 -0.2564 0.0077 1.0000 28.000 1.1506 0.51869 0.51751 -0.2590 0.0074 1.0000 28.500 1.1525 0.52965 0.52851 -0.2608 0.0072 1.0000 29.000 1.1530 0.54623 0.54509 -0.2642 0.0069 1.0000 29.500 1.1541 0.55952 0.55840 -0.2668 0.0065 1.0000 30.000 1.1548 0.57264 0.57156 -0.2693 0.0060 1.0000 30.500 1.1550 0.58527 0.58421 -0.2717 0.0057 1.0000 31.000 1.1548 0.59745 0.59642 -0.2740 0.0055 1.0000 31.500 1.1540 0.60913 0.60814 -0.2761 0.0053 1.0000 32.000 1.1532 0.62211 0.62114 -0.2782 0.0052 1.0000 32.500 1.1523 0.63618 0.63523 -0.2808 0.0052 1.0000 33.000 1.1513 0.64956 0.64864 -0.2831 0.0051 1.0000 33.500 1.1502 0.66274 0.66184 -0.2853 0.0048 1.0000 34.000 1.1484 0.67542 0.67455 -0.2874 0.0043 1.0000 34.500 1.1460 0.68743 0.68658 -0.2895 0.0041 1.0000 35.000 1.1433 0.69923 0.69842 -0.2916 0.0038 1.0000 35.500 1.1398 0.71049 0.70971 -0.2935 0.0036 1.0000 36.500 1.1332 0.73585 0.73511 -0.2974 0.0034 1.0000 37.000 1.1300 0.74853 0.74781 -0.2993 0.0034 1.0000 37.500 1.1265 0.76084 0.76014 -0.3011 0.0031 1.0000 38.000 1.1221 0.77174 0.77107 -0.3029 0.0030 1.0000 38.500 1.1175 0.78303 0.78239 -0.3046 0.0028 1.0000 39.000 1.1125 0.79354 0.79293 -0.3063 0.0027 1.0000 39.500 1.1071 0.80390 0.80332 -0.3080 0.0024 1.0000 40.000 1.1014 0.81386 0.81331 -0.3096 0.0023 1.0000 40.500 1.0953 0.82334 0.82282 -0.3112 0.0022 1.0000 41.000 1.0889 0.83256 0.83206 -0.3128 0.0021 1.0000 41.500 1.0820 0.84123 0.84076 -0.3142 0.0021 1.0000 43.500 1.0535 0.87601 0.87563 -0.3197 0.0019 1.0000 44.000 1.0465 0.88461 0.88425 -0.3209 0.0019 1.0000 44.500 1.0389 0.89234 0.89200 -0.3221 0.0018 1.0000 45.000 1.0307 0.89892 0.89862 -0.3232 0.0017 1.0000 45.500 1.0224 0.90557 0.90528 -0.3243 0.0015 1.0000 46.000 1.0135 0.91111 0.91085 -0.3254 0.0014 1.0000 46.500 1.0047 0.91703 0.91680 -0.3264 0.0012 1.0000 47.000 0.9954 0.92180 0.92158 -0.3274 0.0011 1.0000 47.500 0.9859 0.92609 0.92590 -0.3283 0.0010 1.0000 48.000 0.9758 0.92924 0.92908 -0.3293 0.0009 1.0000 48.500 0.9652 0.93202 0.93188 -0.3302 0.0009 1.0000 50.500 0.9250 0.94467 0.94460 -0.3329 0.0008 1.0000 51.000 0.9148 0.94681 0.94676 -0.3335 0.0008 1.0000 51.500 0.9039 0.94738 0.94734 -0.3340 0.0008 1.0000 52.000 0.8930 0.94796 0.94795 -0.3345 0.0007 1.0000 52.500 0.8819 0.94772 0.94772 -0.3349 0.0007 1.0000 53.000 0.8704 0.94652 0.94654 -0.3353 0.0006 1.0000 53.500 0.8590 0.94560 0.94564 -0.3357 0.0005 1.0000 54.000 0.8471 0.94318 0.94324 -0.3360 0.0005 1.0000 54.500 0.8353 0.94104 0.94112 -0.3363 0.0004 1.0000 55.000 0.8232 0.93787 0.93797 -0.3366 0.0003 1.0000 55.500 0.8109 0.93388 0.93400 -0.3367 0.0003 1.0000 56.000 0.7983 0.92966 0.92979 -0.3370 0.0002 1.0000 56.500 0.7855 0.92453 0.92468 -0.3372 0.0002 1.0000 58.500 0.7361 0.90406 0.90426 -0.3369 0.0002 1.0000 59.000 0.7236 0.89784 0.89806 -0.3367 0.0002 1.0000 59.500 0.7108 0.89062 0.89085 -0.3365 0.0001 1.0000 60.000 0.6979 0.88299 0.88323 -0.3363 0.0001 1.0000