Airfoil: S1223 Builder: Y. Tinel Comment: upper surface vortex generator type "A" @ x/c = 17% Number of Reynolds #'s: 7 Average Reynolds #: 59800 Number of angles of attack: 65 alpha / Cl / Cm -8.87 -0.151 -0.2900 -7.77 -0.117 -0.2900 -6.84 -0.090 -0.2900 -5.78 -0.032 -0.2900 -4.84 0.033 -0.2900 -3.80 0.172 -0.2900 -2.70 0.398 -0.2900 -1.67 0.712 -0.2900 -0.61 0.844 -0.2900 0.38 0.950 -0.2900 1.48 1.047 -0.2900 2.43 1.086 -0.2900 3.44 1.126 -0.2900 4.50 1.206 -0.2900 5.50 1.270 -0.2900 6.51 1.358 -0.2900 7.57 1.429 -0.2900 8.60 1.495 -0.2900 9.56 1.539 -0.2900 10.61 1.596 -0.2900 11.58 1.639 -0.2900 12.62 1.697 -0.2900 13.68 1.772 -0.2900 14.69 1.807 -0.2900 15.67 1.860 -0.2900 16.56 1.418 -0.2900 17.52 1.370 -0.2900 18.52 1.435 -0.2900 19.54 1.480 -0.2900 20.56 1.489 -0.2900 21.55 1.523 -0.2900 22.60 1.544 -0.2900 23.58 1.567 -0.2900 22.70 1.577 -0.2900 21.68 1.489 -0.2900 20.69 1.469 -0.2900 19.76 1.475 -0.2900 18.75 1.422 -0.2900 17.66 1.361 -0.2900 16.65 1.330 -0.2900 15.65 1.296 -0.2900 14.71 1.204 -0.2900 13.66 1.210 -0.2900 12.73 1.279 -0.2900 11.71 1.293 -0.2900 10.69 1.356 -0.2900 9.82 1.571 -0.2900 8.74 1.513 -0.2900 7.79 1.449 -0.2900 6.76 1.384 -0.2900 5.72 1.310 -0.2900 4.77 1.229 -0.2900 3.71 1.152 -0.2900 2.69 1.112 -0.2900 1.69 1.060 -0.2900 0.63 0.982 -0.2900 -0.37 0.871 -0.2900 -1.41 0.751 -0.2900 -2.49 0.486 -0.2900 -3.60 0.193 -0.2900 -4.59 0.062 -0.2900 -5.61 -0.033 -0.2900 -6.65 -0.084 -0.2900 -7.68 -0.116 -0.2900 -8.69 -0.151 -0.2900 Tabulated from data in file MS00354.DAT & reduced using program Q01.00L Average Reynolds #: 79600 Number of angles of attack: 65 alpha / Cl / Cm -9.19 -0.110 -0.2900 -7.84 -0.065 -0.2900 -6.81 -0.027 -0.2900 -5.86 0.017 -0.2900 -4.76 0.082 -0.2900 -3.72 0.207 -0.2900 -2.65 0.487 -0.2900 -1.57 0.774 -0.2900 -0.58 0.893 -0.2900 0.47 0.990 -0.2900 1.44 1.066 -0.2900 2.53 1.161 -0.2900 3.55 1.230 -0.2900 4.56 1.265 -0.2900 5.56 1.345 -0.2900 6.54 1.402 -0.2900 7.63 1.516 -0.2900 8.60 1.575 -0.2900 9.62 1.637 -0.2900 10.62 1.697 -0.2900 11.69 1.748 -0.2900 12.64 1.780 -0.2900 13.68 1.864 -0.2900 14.76 1.923 -0.2900 15.70 1.957 -0.2900 16.72 1.999 -0.2900 17.52 1.314 -0.2900 18.54 1.326 -0.2900 19.58 1.373 -0.2900 20.57 1.429 -0.2900 21.58 1.406 -0.2900 22.57 1.481 -0.2900 23.59 1.527 -0.2900 22.79 1.543 -0.2900 21.72 1.444 -0.2900 20.73 1.414 -0.2900 19.70 1.373 -0.2900 18.72 1.328 -0.2900 17.65 1.316 -0.2900 16.76 1.292 -0.2900 15.71 1.393 -0.2900 14.74 1.512 -0.2900 13.77 1.499 -0.2900 12.74 1.452 -0.2900 11.80 1.727 -0.2900 10.79 1.681 -0.2900 9.75 1.612 -0.2900 8.80 1.565 -0.2900 7.71 1.478 -0.2900 6.77 1.400 -0.2900 5.74 1.313 -0.2900 4.69 1.259 -0.2900 3.74 1.233 -0.2900 2.70 1.159 -0.2900 1.65 1.068 -0.2900 0.64 0.990 -0.2900 -0.37 0.899 -0.2900 -1.45 0.770 -0.2900 -2.46 0.584 -0.2900 -3.59 0.193 -0.2900 -4.64 0.071 -0.2900 -5.65 0.010 -0.2900 -6.64 -0.033 -0.2900 -7.69 -0.072 -0.2900 -8.73 -0.107 -0.2900 Tabulated from data in file MS00353.DAT & reduced using program Q01.00L Average Reynolds #: 98400 Number of angles of attack: 65 alpha / Cl / Cm -8.89 -0.074 -0.2900 -7.76 -0.030 -0.2900 -6.84 0.009 -0.2900 -5.80 0.043 -0.2900 -4.83 0.100 -0.2900 -3.78 0.211 -0.2900 -2.76 0.431 -0.2900 -1.66 0.794 -0.2900 -0.64 0.917 -0.2900 0.40 1.021 -0.2900 1.54 1.114 -0.2900 2.50 1.200 -0.2900 3.50 1.271 -0.2900 4.49 1.327 -0.2900 5.52 1.392 -0.2900 6.54 1.490 -0.2900 7.59 1.560 -0.2900 8.61 1.633 -0.2900 9.61 1.691 -0.2900 10.64 1.759 -0.2900 11.67 1.806 -0.2900 12.70 1.873 -0.2900 13.69 1.926 -0.2900 14.67 1.970 -0.2900 15.72 2.016 -0.2900 16.72 2.041 -0.2900 17.50 1.279 -0.2900 18.55 1.322 -0.2900 19.56 1.374 -0.2900 20.55 1.404 -0.2900 21.55 1.476 -0.2900 22.57 1.546 -0.2900 23.58 1.526 -0.2900 22.73 1.524 -0.2900 21.78 1.469 -0.2900 20.64 1.409 -0.2900 19.65 1.372 -0.2900 18.62 1.316 -0.2900 17.63 1.310 -0.2900 16.69 1.325 -0.2900 15.65 1.224 -0.2900 14.67 1.409 -0.2900 13.67 1.412 -0.2900 12.78 1.868 -0.2900 11.75 1.814 -0.2900 10.87 1.760 -0.2900 9.82 1.694 -0.2900 8.80 1.633 -0.2900 7.79 1.562 -0.2900 6.78 1.498 -0.2900 5.82 1.421 -0.2900 4.75 1.333 -0.2900 3.72 1.278 -0.2900 2.64 1.194 -0.2900 1.57 1.103 -0.2900 0.57 1.025 -0.2900 -0.35 0.943 -0.2900 -1.36 0.821 -0.2900 -2.53 0.586 -0.2900 -3.57 0.226 -0.2900 -4.59 0.109 -0.2900 -5.59 0.037 -0.2900 -6.63 0.009 -0.2900 -7.65 -0.021 -0.2900 -8.68 -0.059 -0.2900 Tabulated from data in file MS00352.DAT & reduced using program Q01.00L Average Reynolds #: 123900 Number of angles of attack: 65 alpha / Cl / Cm -8.64 -0.035 -0.2900 -7.79 -0.008 -0.2900 -6.75 0.024 -0.2900 -5.82 0.057 -0.2900 -4.77 0.117 -0.2900 -3.77 0.230 -0.2900 -2.70 0.452 -0.2900 -1.53 0.825 -0.2900 -0.54 0.940 -0.2900 0.57 1.054 -0.2900 1.46 1.127 -0.2900 2.54 1.221 -0.2900 3.50 1.293 -0.2900 4.50 1.356 -0.2900 5.52 1.442 -0.2900 6.54 1.518 -0.2900 7.61 1.585 -0.2900 8.52 1.647 -0.2900 9.62 1.714 -0.2900 10.63 1.760 -0.2900 11.67 1.809 -0.2900 12.72 1.872 -0.2900 13.69 1.927 -0.2900 14.71 1.980 -0.2900 15.72 2.031 -0.2900 16.75 2.078 -0.2900 17.70 2.102 -0.2900 18.46 1.338 -0.2900 19.55 1.364 -0.2900 20.46 1.379 -0.2900 21.60 1.449 -0.2900 22.52 1.472 -0.2900 23.55 1.538 -0.2900 22.74 1.491 -0.2900 21.81 1.454 -0.2900 20.67 1.388 -0.2900 19.69 1.336 -0.2900 18.68 1.331 -0.2900 17.67 1.291 -0.2900 16.63 1.279 -0.2900 15.73 1.406 -0.2900 14.72 1.412 -0.2900 13.81 1.546 -0.2900 12.88 1.896 -0.2900 11.86 1.837 -0.2900 10.86 1.786 -0.2900 9.84 1.719 -0.2900 8.85 1.652 -0.2900 7.83 1.593 -0.2900 6.88 1.521 -0.2900 5.85 1.455 -0.2900 4.76 1.365 -0.2900 3.77 1.304 -0.2900 2.77 1.231 -0.2900 1.75 1.138 -0.2900 0.74 1.050 -0.2900 -0.29 0.957 -0.2900 -1.32 0.835 -0.2900 -2.38 0.683 -0.2900 -3.49 0.263 -0.2900 -4.56 0.125 -0.2900 -5.59 0.058 -0.2900 -6.61 0.033 -0.2900 -7.61 -0.009 -0.2900 -8.68 -0.031 -0.2900 Tabulated from data in file MS00346.DAT & reduced using program Q01.00L Average Reynolds #: 147900 Number of angles of attack: 65 alpha / Cl / Cm -8.88 -0.005 -0.2900 -7.75 0.017 -0.2900 -6.73 0.041 -0.2900 -5.75 0.075 -0.2900 -4.79 0.128 -0.2900 -3.76 0.242 -0.2900 -2.71 0.543 -0.2900 -1.57 0.839 -0.2900 -0.49 0.968 -0.2900 0.53 1.071 -0.2900 1.53 1.158 -0.2900 2.55 1.244 -0.2900 3.56 1.324 -0.2900 4.60 1.404 -0.2900 5.60 1.486 -0.2900 6.60 1.560 -0.2900 7.61 1.630 -0.2900 8.67 1.705 -0.2900 9.70 1.774 -0.2900 10.71 1.830 -0.2900 11.73 1.892 -0.2900 12.66 1.933 -0.2900 13.73 1.977 -0.2900 14.75 2.036 -0.2900 15.80 2.092 -0.2900 16.71 2.136 -0.2900 17.71 2.155 -0.2900 18.72 2.182 -0.2900 19.74 2.191 -0.2900 20.59 1.398 -0.2900 21.54 1.465 -0.2900 22.57 1.487 -0.2900 23.54 1.512 -0.2900 22.79 1.479 -0.2900 21.68 1.410 -0.2900 20.77 1.414 -0.2900 19.77 1.371 -0.2900 18.76 1.344 -0.2900 17.75 1.350 -0.2900 16.81 1.443 -0.2900 15.81 1.539 -0.2900 14.92 2.071 -0.2900 13.80 2.004 -0.2900 12.81 1.945 -0.2900 11.79 1.886 -0.2900 10.85 1.838 -0.2900 9.73 1.759 -0.2900 8.78 1.695 -0.2900 7.72 1.618 -0.2900 6.83 1.561 -0.2900 5.78 1.482 -0.2900 4.80 1.405 -0.2900 3.64 1.314 -0.2900 2.66 1.241 -0.2900 1.70 1.155 -0.2900 0.66 1.064 -0.2900 -0.36 0.959 -0.2900 -1.43 0.832 -0.2900 -2.42 0.694 -0.2900 -3.55 0.251 -0.2900 -4.65 0.116 -0.2900 -5.71 0.067 -0.2900 -6.71 0.036 -0.2900 -7.73 0.010 -0.2900 -8.74 -0.012 -0.2900 Tabulated from data in file MS00350.DAT & reduced using program Q01.00L Average Reynolds #: 173200 Number of angles of attack: 65 alpha / Cl / Cm -8.86 0.000 -0.2900 -7.79 0.029 -0.2900 -6.81 0.047 -0.2900 -5.77 0.079 -0.2900 -4.84 0.127 -0.2900 -3.79 0.216 -0.2900 -2.72 0.496 -0.2900 -1.41 0.864 -0.2900 -0.42 0.980 -0.2900 0.61 1.088 -0.2900 1.64 1.180 -0.2900 2.54 1.257 -0.2900 3.58 1.344 -0.2900 4.55 1.415 -0.2900 5.56 1.494 -0.2900 6.60 1.578 -0.2900 7.60 1.652 -0.2900 8.70 1.727 -0.2900 9.60 1.792 -0.2900 10.73 1.863 -0.2900 11.62 1.917 -0.2900 12.62 1.961 -0.2900 13.69 2.023 -0.2900 14.68 2.070 -0.2900 15.66 2.127 -0.2900 16.72 2.174 -0.2900 17.65 2.200 -0.2900 18.75 2.224 -0.2900 19.31 1.745 -0.2900 20.47 1.387 -0.2900 21.64 1.440 -0.2900 22.48 1.483 -0.2900 23.46 1.528 -0.2900 22.57 1.482 -0.2900 21.58 1.444 -0.2900 20.40 1.393 -0.2900 19.43 1.379 -0.2900 18.42 1.430 -0.2900 17.56 1.418 -0.2900 16.62 1.499 -0.2900 15.65 1.635 -0.2900 14.85 2.099 -0.2900 13.85 2.037 -0.2900 12.89 1.989 -0.2900 11.79 1.925 -0.2900 10.81 1.861 -0.2900 9.78 1.793 -0.2900 8.83 1.724 -0.2900 7.81 1.658 -0.2900 6.68 1.576 -0.2900 5.65 1.500 -0.2900 4.71 1.424 -0.2900 3.58 1.338 -0.2900 2.62 1.260 -0.2900 1.65 1.172 -0.2900 0.64 1.080 -0.2900 -0.39 0.972 -0.2900 -1.45 0.846 -0.2900 -2.41 0.715 -0.2900 -3.58 0.245 -0.2900 -4.65 0.128 -0.2900 -5.55 0.088 -0.2900 -6.59 0.060 -0.2900 -7.59 0.022 -0.2900 -8.64 0.003 -0.2900 Tabulated from data in file MS00351.DAT & reduced using program Q01.00L Average Reynolds #: 197200 Number of angles of attack: 65 alpha / Cl / Cm -9.24 -0.004 -0.2900 -7.85 0.032 -0.2900 -6.82 0.049 -0.2900 -5.81 0.076 -0.2900 -4.76 0.113 -0.2900 -3.85 0.208 -0.2900 -2.68 0.480 -0.2900 -1.54 0.828 -0.2900 -0.49 0.953 -0.2900 0.64 1.071 -0.2900 1.67 1.165 -0.2900 2.56 1.243 -0.2900 3.64 1.337 -0.2900 4.76 1.422 -0.2900 5.71 1.500 -0.2900 6.73 1.576 -0.2900 7.74 1.651 -0.2900 8.70 1.718 -0.2900 9.76 1.788 -0.2900 10.78 1.851 -0.2900 11.74 1.907 -0.2900 12.75 1.958 -0.2900 13.75 2.016 -0.2900 14.72 2.080 -0.2900 15.78 2.140 -0.2900 16.73 2.173 -0.2900 17.77 2.216 -0.2900 18.82 2.249 -0.2900 19.76 2.271 -0.2900 20.49 1.384 -0.2900 21.42 1.408 -0.2900 22.52 1.468 -0.2900 23.56 1.477 -0.2900 22.69 1.472 -0.2900 21.65 1.414 -0.2900 20.71 1.369 -0.2900 19.68 1.345 -0.2900 18.75 1.377 -0.2900 17.68 1.467 -0.2900 16.79 1.554 -0.2900 16.08 2.165 -0.2900 14.89 2.102 -0.2900 13.91 2.041 -0.2900 12.78 1.987 -0.2900 11.89 1.931 -0.2900 10.83 1.868 -0.2900 9.72 1.786 -0.2900 8.71 1.712 -0.2900 7.57 1.636 -0.2900 6.67 1.562 -0.2900 5.42 1.469 -0.2900 4.59 1.401 -0.2900 3.69 1.334 -0.2900 2.62 1.244 -0.2900 1.63 1.151 -0.2900 0.58 1.054 -0.2900 -0.51 0.936 -0.2900 -1.52 0.816 -0.2900 -2.51 0.677 -0.2900 -3.52 0.233 -0.2900 -4.59 0.122 -0.2900 -5.59 0.075 -0.2900 -6.59 0.042 -0.2900 -7.64 0.017 -0.2900 -8.64 0.004 -0.2900 Tabulated from data in file MS00344.DAT & reduced using program Q01.00L File s1223vg1.lft created on 12-05-1997 at 15:25:51 using program FORMAT