XFOIL Version 6.96 Calculated polar for: GOE 234 (MVA CA5) AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -9.500 -0.0342 0.09908 0.09372 -0.1013 0.9297 0.0546 -9.250 -0.0213 0.09508 0.08967 -0.1045 0.9257 0.0539 -9.000 -0.0251 0.09102 0.08562 -0.1065 0.9157 0.0543 -8.750 0.0027 0.09099 0.08558 -0.1057 0.9121 0.0568 -8.500 0.0082 0.08791 0.08250 -0.1071 0.9048 0.0570 -8.250 0.0094 0.08368 0.07826 -0.1095 0.8972 0.0562 -8.000 -0.0187 0.07510 0.06969 -0.1141 0.8856 0.0544 -7.750 0.0001 0.07413 0.06870 -0.1143 0.8806 0.0552 -7.500 0.0137 0.07193 0.06649 -0.1159 0.8753 0.0563 -7.000 0.0461 0.04005 0.03361 -0.1746 0.8563 0.0571 -6.750 0.1014 0.03557 0.02869 -0.1883 0.8517 0.0586 -6.500 0.1573 0.03235 0.02501 -0.1992 0.8484 0.0613 -6.250 0.2070 0.03015 0.02239 -0.2065 0.8455 0.0631 -6.000 0.2295 0.02968 0.02198 -0.2048 0.8401 0.0643 -5.750 0.2531 0.02939 0.02171 -0.2035 0.8337 0.0657 -5.500 0.2819 0.02900 0.02128 -0.2031 0.8294 0.0677 -5.250 0.3148 0.02851 0.02067 -0.2037 0.8262 0.0708 -5.000 0.3395 0.02841 0.02051 -0.2032 0.8183 0.0731 -4.750 0.3619 0.02864 0.02083 -0.2008 0.8129 0.0754 -4.500 0.3939 0.02843 0.02060 -0.2012 0.8091 0.0785 -4.250 0.4239 0.02823 0.02036 -0.2021 0.8024 0.0827 -4.000 0.4601 0.02772 0.01990 -0.2048 0.7964 0.0893 -3.750 0.5057 0.02671 0.01893 -0.2099 0.7921 0.0998 -3.500 0.5551 0.02555 0.01810 -0.2165 0.7880 0.1553 -3.250 0.5629 0.02721 0.02015 -0.2103 0.7794 0.1888 -3.000 0.5977 0.02726 0.02005 -0.2119 0.7743 0.2312 -2.750 0.6390 0.02689 0.01942 -0.2155 0.7699 0.2563 -2.500 0.6679 0.02708 0.01950 -0.2164 0.7618 0.2698 -2.000 0.7227 0.02774 0.01999 -0.2151 0.7516 0.2873 -1.750 0.7538 0.02775 0.01989 -0.2167 0.7436 0.2993 -1.500 0.7735 0.02830 0.02047 -0.2138 0.7381 0.3035 -1.250 0.8094 0.02810 0.02011 -0.2160 0.7331 0.3152 -1.000 0.8303 0.02834 0.02038 -0.2145 0.7254 0.3179 -0.750 0.8611 0.02808 0.02004 -0.2152 0.7202 0.3215 -0.500 0.9026 0.02750 0.01924 -0.2192 0.7147 0.3303 -0.250 0.9253 0.02761 0.01938 -0.2182 0.7075 0.3323 0.000 0.9533 0.02752 0.01925 -0.2179 0.7024 0.3359 0.250 0.9830 0.02747 0.01914 -0.2187 0.6961 0.3425 0.500 1.0140 0.02731 0.01892 -0.2198 0.6894 0.3477 0.750 1.0442 0.02707 0.01862 -0.2202 0.6843 0.3501 1.000 1.0700 0.02706 0.01861 -0.2201 0.6759 0.3529 1.250 1.1033 0.02662 0.01804 -0.2212 0.6677 0.3555 1.500 1.1321 0.02639 0.01773 -0.2218 0.6559 0.3578 1.750 1.1671 0.02596 0.01710 -0.2236 0.6454 0.3617 2.000 1.1928 0.02587 0.01700 -0.2231 0.6353 0.3632 2.250 1.2200 0.02584 0.01695 -0.2230 0.6276 0.3648 2.500 1.2469 0.02585 0.01695 -0.2231 0.6198 0.3662 2.750 1.2774 0.02573 0.01676 -0.2236 0.6135 0.3678 3.000 1.3020 0.02587 0.01693 -0.2234 0.6047 0.3695 3.250 1.3319 0.02580 0.01678 -0.2239 0.5975 0.3716 3.500 1.3570 0.02595 0.01695 -0.2237 0.5886 0.3744 3.750 1.3862 0.02595 0.01685 -0.2242 0.5806 0.3775 4.000 1.4090 0.02615 0.01712 -0.2234 0.5719 0.3788 4.250 1.4341 0.02626 0.01725 -0.2229 0.5636 0.3801 4.500 1.4572 0.02648 0.01751 -0.2222 0.5548 0.3816 4.750 1.4812 0.02665 0.01769 -0.2216 0.5459 0.3833 5.000 1.5032 0.02692 0.01799 -0.2208 0.5365 0.3852 5.250 1.5267 0.02712 0.01818 -0.2201 0.5271 0.3876 5.500 1.5466 0.02747 0.01858 -0.2189 0.5166 0.3904 5.750 1.5691 0.02772 0.01878 -0.2180 0.5066 0.3931 6.000 1.5853 0.02814 0.01931 -0.2161 0.4950 0.3947 6.250 1.6018 0.02857 0.01979 -0.2142 0.4834 0.3964 6.500 1.6185 0.02899 0.02020 -0.2124 0.4717 0.3981 6.750 1.6309 0.02955 0.02080 -0.2099 0.4590 0.3998 7.000 1.6398 0.03018 0.02148 -0.2068 0.4466 0.4016 7.250 1.6512 0.03086 0.02214 -0.2042 0.4345 0.4036 7.500 1.6638 0.03160 0.02285 -0.2020 0.4224 0.4061 7.750 1.6750 0.03249 0.02376 -0.1997 0.4099 0.4086 8.000 1.6862 0.03339 0.02470 -0.1974 0.3986 0.4104 8.500 1.7063 0.03543 0.02675 -0.1927 0.3763 0.4146 8.750 1.7157 0.03656 0.02787 -0.1904 0.3658 0.4167 9.000 1.7249 0.03774 0.02901 -0.1882 0.3558 0.4188 9.250 1.7339 0.03900 0.03031 -0.1860 0.3464 0.4209 9.500 1.7436 0.04023 0.03148 -0.1840 0.3381 0.4230 9.750 1.7524 0.04156 0.03292 -0.1820 0.3301 0.4249 10.000 1.7618 0.04284 0.03422 -0.1800 0.3231 0.4271 10.250 1.7705 0.04422 0.03567 -0.1781 0.3162 0.4297 10.500 1.7780 0.04571 0.03724 -0.1761 0.3091 0.4323 10.750 1.7870 0.04708 0.03859 -0.1742 0.3029 0.4352 11.000 1.7935 0.04875 0.04041 -0.1724 0.2965 0.4377 11.250 1.8012 0.05029 0.04201 -0.1706 0.2908 0.4399 11.500 1.8092 0.05180 0.04356 -0.1689 0.2853 0.4418 11.750 1.8128 0.05376 0.04572 -0.1670 0.2791 0.4437 12.000 1.8161 0.05569 0.04769 -0.1651 0.2724 0.4457 12.250 1.8177 0.05787 0.04999 -0.1633 0.2657 0.4481 12.500 1.8176 0.06029 0.05255 -0.1616 0.2586 0.4507 12.750 1.8206 0.06236 0.05460 -0.1599 0.2525 0.4537 13.000 1.8188 0.06520 0.05769 -0.1585 0.2458 0.4559 13.250 1.8176 0.06793 0.06056 -0.1571 0.2390 0.4581 13.500 1.8156 0.07083 0.06357 -0.1558 0.2320 0.4605 13.750 1.8095 0.07440 0.06731 -0.1547 0.2234 0.4626 14.000 1.8042 0.07791 0.07092 -0.1537 0.2154 0.4648 14.250 1.7972 0.08188 0.07507 -0.1531 0.2066 0.4668 14.500 1.7883 0.08621 0.07954 -0.1526 0.1964 0.4687 14.750 1.7771 0.09101 0.08446 -0.1524 0.1841 0.4703 15.000 1.7658 0.09599 0.08962 -0.1525 0.1675 0.4717 15.250 1.7490 0.10179 0.09542 -0.1529 0.1420 0.4728 15.500 1.7250 0.10878 0.10227 -0.1538 0.1226 0.4734 15.750 1.7013 0.11600 0.10942 -0.1551 0.1090 0.4740