Airfoil: E374 (B) Builder: M. Bame Comment: clean Number of Reynolds #'s: 4 Average Reynolds #: 60300 Number of angles of attack: 49 alpha / Cl / Cm -6.65 -0.383 -0.0420 -5.36 -0.341 -0.0420 -4.38 -0.299 -0.0420 -3.38 -0.238 -0.0420 -2.35 -0.144 -0.0420 -1.33 -0.038 -0.0420 -0.28 0.111 -0.0420 0.74 0.209 -0.0420 1.74 0.293 -0.0420 2.83 0.363 -0.0420 3.79 0.458 -0.0420 4.86 0.641 -0.0420 5.92 0.753 -0.0420 6.95 0.854 -0.0420 7.92 0.924 -0.0420 8.98 0.949 -0.0420 9.98 0.984 -0.0420 10.95 1.018 -0.0420 11.98 1.039 -0.0420 12.99 1.035 -0.0420 13.98 0.997 -0.0420 14.96 0.871 -0.0420 15.92 0.859 -0.0420 16.92 0.847 -0.0420 17.90 0.823 -0.0420 16.90 0.881 -0.0420 15.93 0.888 -0.0420 14.94 0.926 -0.0420 13.95 0.996 -0.0420 12.96 1.010 -0.0420 11.95 1.029 -0.0420 10.94 1.013 -0.0420 9.94 0.975 -0.0420 8.91 0.940 -0.0420 7.92 0.919 -0.0420 6.91 0.837 -0.0420 5.90 0.742 -0.0420 4.84 0.616 -0.0420 3.80 0.443 -0.0420 2.77 0.345 -0.0420 1.72 0.284 -0.0420 0.72 0.197 -0.0420 -0.28 0.085 -0.0420 -1.32 -0.055 -0.0420 -2.38 -0.158 -0.0420 -3.40 -0.256 -0.0420 -4.42 -0.317 -0.0420 -5.40 -0.362 -0.0420 -6.46 -0.413 -0.0420 Tabulated from data in file CL00615.DAT & reduced using program Q02.00L Average Reynolds #: 100700 Number of angles of attack: 49 alpha / Cl / Cm -6.49 -0.430 -0.0420 -5.28 -0.378 -0.0420 -4.26 -0.279 -0.0420 -3.21 -0.134 -0.0420 -2.21 0.018 -0.0420 -1.23 0.146 -0.0420 -0.10 0.255 -0.0420 0.87 0.331 -0.0420 1.87 0.410 -0.0420 2.88 0.501 -0.0420 3.91 0.605 -0.0420 4.98 0.713 -0.0420 6.06 0.813 -0.0420 7.00 0.895 -0.0420 8.07 0.950 -0.0420 9.10 0.979 -0.0420 10.11 1.016 -0.0420 11.10 1.043 -0.0420 12.06 1.053 -0.0420 13.10 1.046 -0.0420 14.03 0.976 -0.0420 15.01 0.923 -0.0420 16.05 0.888 -0.0420 16.96 0.882 -0.0420 18.05 0.859 -0.0420 16.78 0.874 -0.0420 15.79 0.925 -0.0420 14.78 0.936 -0.0420 13.82 1.008 -0.0420 12.87 1.025 -0.0420 11.89 1.043 -0.0420 10.88 1.028 -0.0420 9.88 0.998 -0.0420 8.90 0.960 -0.0420 7.83 0.928 -0.0420 6.85 0.870 -0.0420 5.77 0.774 -0.0420 4.82 0.683 -0.0420 3.76 0.570 -0.0420 2.72 0.469 -0.0420 1.64 0.371 -0.0420 0.70 0.297 -0.0420 -0.38 0.220 -0.0420 -1.42 0.100 -0.0420 -2.38 -0.034 -0.0420 -3.44 -0.180 -0.0420 -4.52 -0.313 -0.0420 -5.50 -0.387 -0.0420 -6.49 -0.431 -0.0420 Tabulated from data in file CL00617.DAT & reduced using program Q02.00L Average Reynolds #: 201300 Number of angles of attack: 49 alpha / Cl / Cm -6.46 -0.436 -0.0420 -5.26 -0.276 -0.0420 -4.12 -0.150 -0.0420 -3.14 -0.078 -0.0420 -2.16 -0.004 -0.0420 -1.18 0.080 -0.0420 -0.13 0.236 -0.0420 0.92 0.344 -0.0420 1.93 0.437 -0.0420 2.95 0.534 -0.0420 3.99 0.637 -0.0420 5.00 0.737 -0.0420 6.05 0.835 -0.0420 7.15 0.910 -0.0420 8.02 0.942 -0.0420 9.02 0.985 -0.0420 10.11 1.021 -0.0420 11.03 1.043 -0.0420 12.14 1.062 -0.0420 13.13 1.095 -0.0420 14.02 1.056 -0.0420 15.12 0.971 -0.0420 16.09 0.919 -0.0420 17.16 0.900 -0.0420 18.18 0.886 -0.0420 16.69 0.903 -0.0420 15.79 0.932 -0.0420 14.74 0.978 -0.0420 13.83 1.094 -0.0420 12.82 1.086 -0.0420 11.95 1.053 -0.0420 10.92 1.036 -0.0420 9.90 1.012 -0.0420 8.83 0.972 -0.0420 7.84 0.930 -0.0420 6.85 0.891 -0.0420 5.76 0.800 -0.0420 4.70 0.699 -0.0420 3.78 0.607 -0.0420 2.68 0.500 -0.0420 1.64 0.403 -0.0420 0.58 0.306 -0.0420 -0.43 0.169 -0.0420 -1.48 0.048 -0.0420 -2.47 -0.040 -0.0420 -3.56 -0.116 -0.0420 -4.50 -0.192 -0.0420 -5.54 -0.321 -0.0420 -6.63 -0.449 -0.0420 Tabulated from data in file CL00619.DAT & reduced using program Q02.00L Average Reynolds #: 301900 Number of angles of attack: 49 alpha / Cl / Cm -6.40 -0.386 -0.0420 -5.23 -0.256 -0.0420 -4.14 -0.169 -0.0420 -3.22 -0.093 -0.0420 -2.11 -0.006 -0.0420 -1.22 0.068 -0.0420 -0.17 0.185 -0.0420 0.90 0.341 -0.0420 1.96 0.442 -0.0420 2.99 0.539 -0.0420 3.96 0.635 -0.0420 4.92 0.729 -0.0420 6.05 0.831 -0.0420 6.99 0.889 -0.0420 8.06 0.940 -0.0420 8.99 0.984 -0.0420 10.03 1.022 -0.0420 11.05 1.045 -0.0420 12.04 1.128 -0.0420 12.96 1.107 -0.0420 14.08 1.080 -0.0420 15.03 1.026 -0.0420 15.93 0.914 -0.0420 16.98 0.899 -0.0420 17.93 0.894 -0.0420 16.82 0.908 -0.0420 15.76 0.943 -0.0420 14.76 1.045 -0.0420 13.78 1.091 -0.0420 12.99 1.103 -0.0420 11.91 1.101 -0.0420 10.91 1.036 -0.0420 9.91 1.011 -0.0420 8.89 0.973 -0.0420 7.88 0.925 -0.0420 6.85 0.878 -0.0420 5.83 0.807 -0.0420 4.80 0.710 -0.0420 3.70 0.604 -0.0420 2.74 0.510 -0.0420 1.69 0.410 -0.0420 0.67 0.311 -0.0420 -0.42 0.143 -0.0420 -1.45 0.044 -0.0420 -2.54 -0.044 -0.0420 -3.59 -0.130 -0.0420 -4.51 -0.201 -0.0420 -5.62 -0.297 -0.0420 -6.62 -0.410 -0.0420 Tabulated from data in file CL00621.DAT & reduced using program Q02.00L File e374b.lft created on 09-12-1997 at 13:46:17 using program FORMAT