Airfoil: SD7037 (B) Builder: D. Thompson Comment: clean: flap = 10 degs Number of Reynolds #'s: 4 Average Reynolds #: 60000 Number of angles of attack: 49 alpha / Cl / Cm -5.97 -0.115 -0.1200 -4.23 0.058 -0.1200 -3.36 0.133 -0.1200 -2.30 0.217 -0.1200 -1.24 0.320 -0.1200 -0.53 0.389 -0.1200 0.55 0.491 -0.1200 1.65 0.645 -0.1200 2.75 0.830 -0.1200 3.84 0.996 -0.1200 4.95 1.081 -0.1200 5.67 1.126 -0.1200 6.78 1.180 -0.1200 7.91 1.224 -0.1200 9.05 1.273 -0.1200 9.77 1.302 -0.1200 10.85 1.339 -0.1200 11.91 1.341 -0.1200 12.91 1.113 -0.1200 13.85 1.096 -0.1200 14.95 1.090 -0.1200 16.02 1.133 -0.1200 16.73 1.114 -0.1200 17.85 1.111 -0.1200 18.99 1.130 -0.1200 17.10 1.140 -0.1200 16.15 1.093 -0.1200 15.22 1.083 -0.1200 14.04 1.124 -0.1200 13.16 1.115 -0.1200 12.26 1.161 -0.1200 11.09 1.342 -0.1200 10.34 1.332 -0.1200 9.16 1.294 -0.1200 8.25 1.255 -0.1200 7.32 1.220 -0.1200 6.10 1.168 -0.1200 5.14 1.106 -0.1200 4.21 1.041 -0.1200 3.27 0.937 -0.1200 2.04 0.698 -0.1200 1.10 0.586 -0.1200 -0.11 0.444 -0.1200 -1.02 0.367 -0.1200 -1.95 0.271 -0.1200 -3.18 0.180 -0.1200 -4.11 0.098 -0.1200 -5.07 0.009 -0.1200 -5.99 -0.084 -0.1200 Tabulated from data in file CL00814.DAT & reduced using program Q02.00L Average Reynolds #: 100400 Number of angles of attack: 49 alpha / Cl / Cm -5.93 0.001 -0.1200 -4.44 0.113 -0.1200 -3.42 0.215 -0.1200 -2.55 0.291 -0.1200 -1.41 0.385 -0.1200 -0.55 0.467 -0.1200 0.58 0.589 -0.1200 1.74 0.798 -0.1200 2.61 0.922 -0.1200 3.73 1.022 -0.1200 4.87 1.115 -0.1200 5.77 1.180 -0.1200 6.95 1.254 -0.1200 7.85 1.284 -0.1200 8.83 1.320 -0.1200 9.93 1.361 -0.1200 10.81 1.378 -0.1200 11.83 1.388 -0.1200 12.88 1.365 -0.1200 13.74 1.079 -0.1200 14.70 1.104 -0.1200 15.84 1.157 -0.1200 16.84 1.103 -0.1200 17.76 1.149 -0.1200 18.95 1.127 -0.1200 17.14 1.140 -0.1200 16.34 1.106 -0.1200 15.18 1.097 -0.1200 14.37 1.097 -0.1200 13.29 1.109 -0.1200 12.31 1.293 -0.1200 11.37 1.375 -0.1200 10.30 1.358 -0.1200 9.46 1.332 -0.1200 8.37 1.290 -0.1200 7.27 1.251 -0.1200 6.36 1.202 -0.1200 5.20 1.121 -0.1200 4.27 1.047 -0.1200 3.15 0.949 -0.1200 2.23 0.861 -0.1200 1.26 0.692 -0.1200 0.15 0.519 -0.1200 -0.95 0.395 -0.1200 -1.91 0.314 -0.1200 -2.88 0.246 -0.1200 -4.00 0.135 -0.1200 -4.94 0.044 -0.1200 -6.00 -0.043 -0.1200 Tabulated from data in file CL00816.DAT & reduced using program Q02.00L Average Reynolds #: 200100 Number of angles of attack: 49 alpha / Cl / Cm -6.00 0.099 -0.1200 -4.34 0.256 -0.1200 -3.32 0.346 -0.1200 -2.33 0.447 -0.1200 -1.34 0.540 -0.1200 -0.37 0.585 -0.1200 0.47 0.717 -0.1200 1.74 0.864 -0.1200 2.73 0.946 -0.1200 3.70 1.027 -0.1200 4.66 1.103 -0.1200 5.77 1.179 -0.1200 6.78 1.235 -0.1200 7.61 1.275 -0.1200 8.74 1.327 -0.1200 9.76 1.372 -0.1200 10.75 1.400 -0.1200 11.69 1.414 -0.1200 12.71 1.399 -0.1200 13.72 1.362 -0.1200 14.54 1.117 -0.1200 15.81 1.146 -0.1200 16.82 1.129 -0.1200 17.70 1.138 -0.1200 18.63 1.145 -0.1200 17.06 1.181 -0.1200 16.23 1.137 -0.1200 15.06 1.124 -0.1200 14.24 1.135 -0.1200 13.38 1.376 -0.1200 12.42 1.408 -0.1200 11.33 1.413 -0.1200 10.28 1.389 -0.1200 9.27 1.350 -0.1200 8.34 1.304 -0.1200 7.16 1.249 -0.1200 6.25 1.203 -0.1200 5.14 1.133 -0.1200 4.25 1.066 -0.1200 3.20 0.978 -0.1200 2.10 0.890 -0.1200 0.93 0.772 -0.1200 0.11 0.648 -0.1200 -1.05 0.573 -0.1200 -2.04 0.476 -0.1200 -2.93 0.387 -0.1200 -4.07 0.275 -0.1200 -5.30 0.160 -0.1200 -6.06 0.091 -0.1200 Tabulated from data in file AG00818.DAT & reduced using program Q02.00L Average Reynolds #: 300100 Number of angles of attack: 49 alpha / Cl / Cm -5.98 0.088 -0.1200 -4.62 0.210 -0.1200 -3.65 0.323 -0.1200 -2.58 0.438 -0.1200 -1.53 0.538 -0.1200 -0.39 0.659 -0.1200 0.56 0.754 -0.1200 1.67 0.851 -0.1200 2.67 0.933 -0.1200 3.66 1.016 -0.1200 4.67 1.095 -0.1200 5.80 1.168 -0.1200 6.77 1.221 -0.1200 7.88 1.281 -0.1200 8.72 1.327 -0.1200 10.00 1.390 -0.1200 10.84 1.417 -0.1200 11.99 1.419 -0.1200 12.83 1.395 -0.1200 13.90 1.352 -0.1200 14.37 1.207 -0.1200 15.49 1.196 -0.1200 16.44 1.184 -0.1200 17.45 1.174 -0.1200 18.44 1.141 -0.1200 17.36 1.148 -0.1200 16.34 1.187 -0.1200 15.30 1.200 -0.1200 14.33 1.262 -0.1200 13.56 1.360 -0.1200 12.20 1.413 -0.1200 11.36 1.424 -0.1200 10.15 1.393 -0.1200 9.16 1.349 -0.1200 8.05 1.288 -0.1200 7.01 1.231 -0.1200 6.24 1.190 -0.1200 5.00 1.114 -0.1200 4.07 1.046 -0.1200 3.21 0.976 -0.1200 2.03 0.876 -0.1200 1.24 0.815 -0.1200 -0.02 0.693 -0.1200 -0.96 0.591 -0.1200 -1.86 0.503 -0.1200 -2.97 0.392 -0.1200 -3.87 0.292 -0.1200 -5.05 0.162 -0.1200 -6.05 0.076 -0.1200 Tabulated from data in file CL00821.DAT & reduced using program Q02.00L File 7037bf10.lft created on 09-12-1997 at 13:46:19 using program FORMAT