Airfoil: MA409 Builder: R. Conney Comment: clean Number of Reynolds #'s: 6 Average Reynolds #: 30600 Number of angles of attack: 49 alpha / Cl / Cm -6.19 -0.431 -0.1150 -4.67 -0.315 -0.1150 -3.85 -0.253 -0.1150 -2.89 -0.177 -0.1150 -1.68 -0.073 -0.1150 -0.84 0.002 -0.1150 0.35 0.122 -0.1150 1.20 0.207 -0.1150 2.36 0.310 -0.1150 3.47 0.442 -0.1150 4.33 0.587 -0.1150 5.55 0.754 -0.1150 6.41 0.815 -0.1150 7.66 0.897 -0.1150 8.51 0.949 -0.1150 9.39 0.998 -0.1150 10.59 1.032 -0.1150 11.46 1.031 -0.1150 12.61 1.006 -0.1150 13.40 0.903 -0.1150 14.52 0.870 -0.1150 15.36 0.885 -0.1150 16.53 0.939 -0.1150 17.65 0.983 -0.1150 18.49 1.012 -0.1150 17.18 0.941 -0.1150 16.13 0.940 -0.1150 15.15 0.915 -0.1150 14.18 0.914 -0.1150 13.17 0.940 -0.1150 12.16 1.038 -0.1150 11.19 1.093 -0.1150 10.17 1.054 -0.1150 9.16 1.021 -0.1150 8.14 0.974 -0.1150 7.11 0.909 -0.1150 6.07 0.832 -0.1150 5.05 0.743 -0.1150 4.02 0.578 -0.1150 3.01 0.414 -0.1150 2.09 0.337 -0.1150 0.97 0.231 -0.1150 0.02 0.137 -0.1150 -1.07 0.036 -0.1150 -2.08 -0.049 -0.1150 -3.08 -0.142 -0.1150 -4.10 -0.230 -0.1150 -5.13 -0.329 -0.1150 -6.17 -0.414 -0.1150 Tabulated from data in file AB00524.DAT & reduced using program Q01.00L Average Reynolds #: 40400 Number of angles of attack: 49 alpha / Cl / Cm -5.85 -0.391 -0.1150 -4.65 -0.279 -0.1150 -3.74 -0.202 -0.1150 -2.82 -0.130 -0.1150 -1.60 -0.027 -0.1150 -0.73 0.052 -0.1150 0.47 0.170 -0.1150 1.41 0.262 -0.1150 2.25 0.334 -0.1150 3.44 0.539 -0.1150 4.35 0.673 -0.1150 5.55 0.781 -0.1150 6.43 0.832 -0.1150 7.39 0.900 -0.1150 8.62 0.970 -0.1150 9.52 1.007 -0.1150 10.41 1.041 -0.1150 11.60 1.067 -0.1150 12.45 1.001 -0.1150 13.55 0.931 -0.1150 14.39 0.910 -0.1150 15.55 0.910 -0.1150 16.42 0.928 -0.1150 17.58 0.933 -0.1150 18.47 1.021 -0.1150 17.12 0.940 -0.1150 16.07 0.918 -0.1150 15.07 0.965 -0.1150 14.26 0.963 -0.1150 13.11 1.010 -0.1150 12.25 1.008 -0.1150 11.18 1.069 -0.1150 10.19 1.048 -0.1150 9.16 1.014 -0.1150 8.15 0.976 -0.1150 7.15 0.919 -0.1150 6.17 0.832 -0.1150 5.21 0.785 -0.1150 4.08 0.672 -0.1150 3.11 0.497 -0.1150 2.00 0.337 -0.1150 1.01 0.252 -0.1150 0.04 0.159 -0.1150 -1.01 0.066 -0.1150 -2.12 -0.041 -0.1150 -3.14 -0.121 -0.1150 -4.16 -0.212 -0.1150 -5.21 -0.313 -0.1150 -6.25 -0.409 -0.1150 Tabulated from data in file AB00525.DAT & reduced using program Q01.00L Average Reynolds #: 61100 Number of angles of attack: 33 alpha / Cl / Cm -6.11 -0.385 -0.1150 -4.30 -0.228 -0.1150 -2.65 -0.100 -0.1150 -1.10 0.037 -0.1150 0.50 0.199 -0.1150 1.99 0.388 -0.1150 3.20 0.570 -0.1150 4.85 0.711 -0.1150 6.30 0.827 -0.1150 8.03 0.926 -0.1150 9.51 1.000 -0.1150 11.16 1.024 -0.1150 12.40 1.010 -0.1150 14.12 0.989 -0.1150 15.64 0.948 -0.1150 16.82 0.938 -0.1150 18.36 0.949 -0.1150 16.57 0.931 -0.1150 15.21 0.984 -0.1150 13.62 1.000 -0.1150 12.21 1.023 -0.1150 10.56 1.011 -0.1150 9.28 0.967 -0.1150 7.46 0.869 -0.1150 6.11 0.789 -0.1150 4.65 0.677 -0.1150 3.18 0.545 -0.1150 1.58 0.295 -0.1150 -0.19 0.118 -0.1150 -1.45 -0.002 -0.1150 -3.17 -0.140 -0.1150 -4.69 -0.257 -0.1150 -6.05 -0.391 -0.1150 Tabulated from data in file MS00176.DAT & reduced using program Q01.00L Average Reynolds #: 101800 Number of angles of attack: 33 alpha / Cl / Cm -6.11 -0.407 -0.1150 -4.37 -0.228 -0.1150 -2.57 -0.086 -0.1150 -1.26 0.029 -0.1150 0.38 0.190 -0.1150 1.78 0.416 -0.1150 3.36 0.587 -0.1150 5.10 0.737 -0.1150 6.38 0.836 -0.1150 8.21 0.948 -0.1150 9.49 1.014 -0.1150 11.15 1.048 -0.1150 12.30 1.012 -0.1150 14.03 0.952 -0.1150 15.73 0.935 -0.1150 17.03 0.922 -0.1150 18.24 0.907 -0.1150 16.83 0.932 -0.1150 15.21 0.958 -0.1150 13.55 0.974 -0.1150 12.16 0.998 -0.1150 10.76 1.037 -0.1150 9.14 0.974 -0.1150 7.69 0.894 -0.1150 6.25 0.804 -0.1150 4.49 0.663 -0.1150 2.99 0.531 -0.1150 1.60 0.386 -0.1150 -0.01 0.143 -0.1150 -1.74 -0.024 -0.1150 -3.17 -0.141 -0.1150 -4.65 -0.259 -0.1150 -6.19 -0.422 -0.1150 Tabulated from data in file JG00178.DAT & reduced using program Q01.00L Average Reynolds #: 203000 Number of angles of attack: 33 alpha / Cl / Cm -5.95 -0.397 -0.1150 -4.40 -0.240 -0.1150 -2.89 -0.116 -0.1150 -1.40 0.056 -0.1150 -0.07 0.221 -0.1150 1.69 0.405 -0.1150 3.26 0.563 -0.1150 4.64 0.689 -0.1150 6.17 0.819 -0.1150 7.63 0.920 -0.1150 9.20 1.009 -0.1150 10.64 1.070 -0.1150 12.20 1.069 -0.1150 13.63 1.036 -0.1150 15.02 0.995 -0.1150 16.59 0.964 -0.1150 18.06 0.941 -0.1150 16.63 0.950 -0.1150 15.16 1.007 -0.1150 13.78 1.050 -0.1150 12.20 1.071 -0.1150 10.92 1.080 -0.1150 9.49 1.020 -0.1150 7.88 0.930 -0.1150 6.32 0.824 -0.1150 4.80 0.695 -0.1150 3.36 0.564 -0.1150 1.78 0.411 -0.1150 0.07 0.231 -0.1150 -1.30 0.063 -0.1150 -2.88 -0.120 -0.1150 -4.49 -0.251 -0.1150 -5.91 -0.399 -0.1150 Tabulated from data in file AB00180.DAT & reduced using program Q01.00L Average Reynolds #: 304000 Number of angles of attack: 33 alpha / Cl / Cm -6.09 -0.406 -0.1150 -4.67 -0.268 -0.1150 -3.19 -0.140 -0.1150 -1.58 0.050 -0.1150 -0.02 0.232 -0.1150 1.43 0.379 -0.1150 3.38 0.570 -0.1150 4.87 0.703 -0.1150 6.28 0.822 -0.1150 7.95 0.945 -0.1150 9.34 1.025 -0.1150 10.80 1.089 -0.1150 11.99 1.091 -0.1150 13.45 1.053 -0.1150 14.97 0.997 -0.1150 16.61 0.988 -0.1150 18.00 0.996 -0.1150 16.80 1.005 -0.1150 15.29 1.005 -0.1150 13.79 1.030 -0.1150 12.39 1.095 -0.1150 11.04 1.084 -0.1150 9.38 1.026 -0.1150 7.83 0.935 -0.1150 6.36 0.828 -0.1150 4.64 0.681 -0.1150 3.15 0.540 -0.1150 1.53 0.383 -0.1150 0.08 0.234 -0.1150 -1.45 0.060 -0.1150 -3.04 -0.132 -0.1150 -4.68 -0.276 -0.1150 -5.94 -0.399 -0.1150 Tabulated from data in file AB00182.DAT & reduced using program Q01.00L File ma409.lft created on 12-05-1997 at 15:25:50 using program FORMAT