Airfoil: S5010 Builder: O. Wilson Comment: clean Number of Reynolds #'s: 4 Average Reynolds #: 60400 Number of angles of attack: 49 alpha / Cl / Cm -7.09 -0.552 -0.0070 -5.71 -0.401 -0.0070 -4.62 -0.298 -0.0070 -3.56 -0.200 -0.0070 -2.56 -0.131 -0.0070 -1.53 0.009 -0.0070 -0.50 0.126 -0.0070 0.52 0.221 -0.0070 1.54 0.310 -0.0070 2.58 0.397 -0.0070 3.62 0.484 -0.0070 4.65 0.569 -0.0070 5.72 0.657 -0.0070 6.54 0.728 -0.0070 7.63 0.823 -0.0070 8.73 0.916 -0.0070 9.55 0.981 -0.0070 10.61 1.058 -0.0070 11.64 1.104 -0.0070 12.64 1.133 -0.0070 13.59 0.893 -0.0070 14.64 0.875 -0.0070 15.71 0.874 -0.0070 16.53 0.910 -0.0070 17.69 0.913 -0.0070 16.13 0.909 -0.0070 15.16 0.885 -0.0070 14.23 0.879 -0.0070 13.14 0.949 -0.0070 12.21 0.962 -0.0070 11.36 1.088 -0.0070 10.12 1.017 -0.0070 9.18 0.942 -0.0070 8.09 0.851 -0.0070 7.13 0.766 -0.0070 6.21 0.683 -0.0070 5.08 0.586 -0.0070 4.18 0.514 -0.0070 3.10 0.423 -0.0070 2.03 0.334 -0.0070 0.95 0.243 -0.0070 -0.12 0.149 -0.0070 -1.00 0.057 -0.0070 -2.08 -0.096 -0.0070 -3.13 -0.181 -0.0070 -4.14 -0.267 -0.0070 -5.21 -0.368 -0.0070 -6.22 -0.467 -0.0070 -7.23 -0.564 -0.0070 Tabulated from data in file CL00765.DAT & reduced using program Q02.00L Average Reynolds #: 100800 Number of angles of attack: 49 alpha / Cl / Cm -7.25 -0.619 -0.0070 -5.57 -0.423 -0.0070 -4.66 -0.323 -0.0070 -3.70 -0.222 -0.0070 -2.70 -0.111 -0.0070 -1.60 -0.034 -0.0070 -0.52 0.071 -0.0070 0.54 0.163 -0.0070 1.59 0.259 -0.0070 2.63 0.354 -0.0070 3.43 0.429 -0.0070 4.56 0.535 -0.0070 5.68 0.639 -0.0070 6.53 0.720 -0.0070 7.70 0.829 -0.0070 8.63 0.911 -0.0070 9.78 1.007 -0.0070 10.61 1.058 -0.0070 11.66 1.098 -0.0070 12.71 1.121 -0.0070 13.66 0.903 -0.0070 14.63 0.881 -0.0070 15.72 0.878 -0.0070 16.56 0.885 -0.0070 17.69 0.892 -0.0070 16.18 0.892 -0.0070 15.18 0.873 -0.0070 14.22 0.922 -0.0070 13.33 1.121 -0.0070 12.19 1.109 -0.0070 11.27 1.078 -0.0070 10.33 1.030 -0.0070 9.25 0.947 -0.0070 8.27 0.858 -0.0070 7.07 0.746 -0.0070 6.00 0.649 -0.0070 5.12 0.572 -0.0070 4.17 0.486 -0.0070 3.07 0.383 -0.0070 1.98 0.282 -0.0070 0.89 0.184 -0.0070 0.00 0.105 -0.0070 -1.09 0.008 -0.0070 -2.17 -0.079 -0.0070 -3.05 -0.156 -0.0070 -4.11 -0.273 -0.0070 -5.18 -0.384 -0.0070 -6.27 -0.514 -0.0070 -7.24 -0.609 -0.0070 Tabulated from data in file AG00767.DAT & reduced using program Q02.00L Average Reynolds #: 201500 Number of angles of attack: 49 alpha / Cl / Cm -7.15 -0.628 -0.0070 -5.68 -0.455 -0.0070 -4.57 -0.345 -0.0070 -3.67 -0.261 -0.0070 -2.64 -0.169 -0.0070 -1.47 -0.060 -0.0070 -0.49 0.020 -0.0070 0.47 0.120 -0.0070 1.51 0.220 -0.0070 2.61 0.321 -0.0070 3.60 0.422 -0.0070 4.39 0.501 -0.0070 5.44 0.629 -0.0070 6.59 0.746 -0.0070 7.51 0.836 -0.0070 8.74 0.952 -0.0070 9.70 1.031 -0.0070 10.65 1.090 -0.0070 11.60 1.122 -0.0070 12.75 1.136 -0.0070 13.65 1.137 -0.0070 14.40 0.932 -0.0070 15.61 0.899 -0.0070 16.60 0.904 -0.0070 17.58 0.892 -0.0070 16.03 0.898 -0.0070 15.02 0.913 -0.0070 14.19 0.946 -0.0070 13.41 1.134 -0.0070 12.27 1.126 -0.0070 11.30 1.107 -0.0070 10.20 1.057 -0.0070 9.25 0.986 -0.0070 8.13 0.883 -0.0070 7.13 0.785 -0.0070 6.12 0.681 -0.0070 5.22 0.588 -0.0070 4.02 0.445 -0.0070 3.04 0.344 -0.0070 2.12 0.250 -0.0070 0.78 0.130 -0.0070 -0.05 0.048 -0.0070 -1.05 -0.053 -0.0070 -2.06 -0.136 -0.0070 -3.09 -0.231 -0.0070 -4.14 -0.324 -0.0070 -5.07 -0.408 -0.0070 -6.06 -0.517 -0.0070 -7.22 -0.646 -0.0070 Tabulated from data in file CL00769.DAT & reduced using program Q02.00L Average Reynolds #: 302300 Number of angles of attack: 49 alpha / Cl / Cm -7.17 -0.645 -0.0070 -5.62 -0.483 -0.0070 -4.67 -0.382 -0.0070 -3.65 -0.285 -0.0070 -2.54 -0.180 -0.0070 -1.55 -0.084 -0.0070 -0.56 -0.000 -0.0070 0.68 0.112 -0.0070 1.48 0.195 -0.0070 2.54 0.333 -0.0070 3.51 0.435 -0.0070 4.64 0.551 -0.0070 5.63 0.653 -0.0070 6.55 0.745 -0.0070 7.59 0.848 -0.0070 8.60 0.945 -0.0070 9.59 1.031 -0.0070 10.69 1.106 -0.0070 11.60 1.140 -0.0070 12.64 1.154 -0.0070 13.72 1.164 -0.0070 14.62 1.160 -0.0070 15.12 0.984 -0.0070 16.58 0.967 -0.0070 17.51 0.944 -0.0070 16.08 0.951 -0.0070 15.21 0.974 -0.0070 14.67 1.165 -0.0070 13.32 1.162 -0.0070 12.25 1.151 -0.0070 11.23 1.129 -0.0070 10.28 1.079 -0.0070 9.17 0.991 -0.0070 8.22 0.903 -0.0070 7.17 0.800 -0.0070 6.07 0.690 -0.0070 5.11 0.593 -0.0070 3.96 0.476 -0.0070 3.04 0.381 -0.0070 2.16 0.286 -0.0070 1.02 0.140 -0.0070 -0.07 0.041 -0.0070 -1.02 -0.043 -0.0070 -2.07 -0.141 -0.0070 -3.07 -0.238 -0.0070 -4.20 -0.343 -0.0070 -5.22 -0.446 -0.0070 -6.13 -0.547 -0.0070 -7.18 -0.651 -0.0070 Tabulated from data in file CL00771.DAT & reduced using program Q02.00L File s5010.lft created on 09-12-1997 at 13:46:18 using program FORMAT