Airfoil: S4083 (B) Builder: J. Thomas Comment: clean Number of Reynolds #'s: 4 Average Reynolds #: 60000 Number of angles of attack: 49 alpha / Cl / Cm -5.93 -0.314 -0.0990 -4.66 -0.175 -0.0990 -3.75 -0.083 -0.0990 -2.60 0.020 -0.0990 -1.66 0.108 -0.0990 -0.51 0.217 -0.0990 0.43 0.375 -0.0990 1.60 0.535 -0.0990 2.48 0.604 -0.0990 3.63 0.704 -0.0990 4.52 0.784 -0.0990 5.71 0.882 -0.0990 6.66 0.959 -0.0990 7.67 1.043 -0.0990 8.69 1.113 -0.0990 9.69 1.171 -0.0990 10.66 1.202 -0.0990 11.63 1.222 -0.0990 12.64 1.222 -0.0990 13.56 1.115 -0.0990 14.63 1.023 -0.0990 15.72 1.026 -0.0990 16.66 1.021 -0.0990 17.61 0.990 -0.0990 18.58 0.993 -0.0990 17.24 1.002 -0.0990 16.15 1.028 -0.0990 15.25 1.036 -0.0990 14.22 1.086 -0.0990 13.20 1.181 -0.0990 12.26 1.223 -0.0990 11.23 1.217 -0.0990 10.35 1.194 -0.0990 9.30 1.152 -0.0990 8.19 1.078 -0.0990 7.23 1.004 -0.0990 6.10 0.913 -0.0990 5.18 0.842 -0.0990 4.08 0.746 -0.0990 3.19 0.673 -0.0990 2.13 0.579 -0.0990 1.04 0.468 -0.0990 0.10 0.300 -0.0990 -1.03 0.165 -0.0990 -2.11 0.066 -0.0990 -3.01 -0.015 -0.0990 -4.14 -0.126 -0.0990 -5.11 -0.240 -0.0990 -6.08 -0.335 -0.0990 Tabulated from data in file CL00639.DAT & reduced using program Q02.00L Average Reynolds #: 100200 Number of angles of attack: 49 alpha / Cl / Cm -6.02 -0.352 -0.0990 -4.73 -0.197 -0.0990 -3.70 -0.074 -0.0990 -2.68 0.022 -0.0990 -1.62 0.124 -0.0990 -0.59 0.290 -0.0990 0.48 0.416 -0.0990 1.53 0.536 -0.0990 2.58 0.635 -0.0990 3.60 0.733 -0.0990 4.63 0.833 -0.0990 5.70 0.929 -0.0990 6.56 1.006 -0.0990 7.69 1.106 -0.0990 8.58 1.167 -0.0990 9.66 1.216 -0.0990 10.71 1.250 -0.0990 11.74 1.260 -0.0990 12.56 1.241 -0.0990 13.68 1.238 -0.0990 14.63 1.055 -0.0990 15.74 1.072 -0.0990 16.55 1.052 -0.0990 17.69 1.037 -0.0990 18.58 1.029 -0.0990 17.27 1.063 -0.0990 16.17 1.032 -0.0990 15.29 1.066 -0.0990 14.31 1.101 -0.0990 13.33 1.218 -0.0990 12.35 1.247 -0.0990 11.31 1.257 -0.0990 10.36 1.236 -0.0990 9.23 1.194 -0.0990 8.20 1.134 -0.0990 7.14 1.050 -0.0990 6.26 0.968 -0.0990 5.20 0.872 -0.0990 4.19 0.778 -0.0990 3.18 0.679 -0.0990 2.18 0.582 -0.0990 1.15 0.483 -0.0990 0.11 0.356 -0.0990 -0.92 0.217 -0.0990 -1.95 0.080 -0.0990 -3.13 -0.031 -0.0990 -4.18 -0.145 -0.0990 -5.20 -0.269 -0.0990 -6.21 -0.367 -0.0990 Tabulated from data in file CL00641.DAT & reduced using program Q02.00L Average Reynolds #: 200300 Number of angles of attack: 49 alpha / Cl / Cm -6.03 -0.368 -0.0990 -4.59 -0.178 -0.0990 -3.58 -0.046 -0.0990 -2.51 0.092 -0.0990 -1.53 0.219 -0.0990 -0.61 0.328 -0.0990 0.42 0.436 -0.0990 1.57 0.567 -0.0990 2.56 0.667 -0.0990 3.48 0.761 -0.0990 4.57 0.870 -0.0990 5.56 0.963 -0.0990 6.71 1.068 -0.0990 7.67 1.140 -0.0990 8.76 1.206 -0.0990 9.66 1.245 -0.0990 10.65 1.267 -0.0990 11.72 1.258 -0.0990 12.71 1.250 -0.0990 13.54 1.226 -0.0990 14.54 1.126 -0.0990 15.54 1.085 -0.0990 16.58 1.162 -0.0990 17.62 1.112 -0.0990 18.58 1.048 -0.0990 17.26 1.134 -0.0990 16.15 1.109 -0.0990 15.29 1.118 -0.0990 14.24 1.144 -0.0990 13.39 1.229 -0.0990 12.38 1.252 -0.0990 11.35 1.260 -0.0990 10.34 1.261 -0.0990 9.34 1.228 -0.0990 8.25 1.172 -0.0990 7.26 1.102 -0.0990 6.21 1.018 -0.0990 5.31 0.930 -0.0990 4.20 0.823 -0.0990 3.09 0.711 -0.0990 2.17 0.618 -0.0990 1.04 0.503 -0.0990 0.08 0.383 -0.0990 -1.00 0.277 -0.0990 -1.93 0.165 -0.0990 -3.10 -0.007 -0.0990 -4.12 -0.117 -0.0990 -5.01 -0.237 -0.0990 -6.12 -0.371 -0.0990 Tabulated from data in file CL00643.DAT & reduced using program Q02.00L Average Reynolds #: 300300 Number of angles of attack: 49 alpha / Cl / Cm -5.87 -0.349 -0.0990 -4.80 -0.201 -0.0990 -3.66 -0.027 -0.0990 -2.73 0.090 -0.0990 -1.73 0.243 -0.0990 -0.62 0.358 -0.0990 0.33 0.447 -0.0990 1.51 0.575 -0.0990 2.56 0.684 -0.0990 3.52 0.785 -0.0990 4.52 0.887 -0.0990 5.57 0.990 -0.0990 6.73 1.090 -0.0990 7.85 1.173 -0.0990 8.79 1.230 -0.0990 9.86 1.278 -0.0990 10.71 1.288 -0.0990 11.76 1.280 -0.0990 12.79 1.268 -0.0990 13.72 1.242 -0.0990 14.47 1.242 -0.0990 15.46 1.204 -0.0990 16.44 1.211 -0.0990 17.48 1.150 -0.0990 18.41 1.075 -0.0990 17.50 1.155 -0.0990 16.33 1.189 -0.0990 15.43 1.200 -0.0990 14.39 1.231 -0.0990 13.49 1.248 -0.0990 12.17 1.277 -0.0990 11.32 1.285 -0.0990 10.35 1.288 -0.0990 9.35 1.254 -0.0990 8.34 1.200 -0.0990 7.15 1.115 -0.0990 6.29 1.047 -0.0990 5.20 0.946 -0.0990 3.99 0.822 -0.0990 3.02 0.724 -0.0990 2.11 0.626 -0.0990 1.07 0.517 -0.0990 -0.12 0.401 -0.0990 -1.04 0.309 -0.0990 -1.97 0.209 -0.0990 -2.97 0.048 -0.0990 -4.09 -0.095 -0.0990 -5.16 -0.254 -0.0990 -5.97 -0.356 -0.0990 Tabulated from data in file CL00645.DAT & reduced using program Q02.00L File s4083b.lft created on 09-12-1997 at 13:46:18 using program FORMAT