Airfoil: SD7037 (C) Builder: D. Brengman Comment: clean Number of Reynolds #'s: 4 Average Reynolds #: 60300 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -4.31 -0.207 0.0307 0.0337 0.0311 0.0285 0.0296 -2.85 -0.087 0.0233 0.0228 0.0230 0.0229 0.0244 -1.29 0.057 0.0193 0.0161 0.0192 0.0175 0.0244 0.26 0.237 0.0221 0.0217 0.0237 0.0244 0.0189 1.83 0.461 0.0269 0.0260 0.0269 0.0293 0.0254 3.37 0.664 0.0302 0.0272 0.0297 0.0368 0.0271 4.93 0.822 0.0278 0.0224 0.0290 0.0352 0.0245 6.45 0.958 0.0245 0.0218 0.0233 0.0257 0.0273 7.95 1.071 0.0276 0.0257 0.0299 0.0305 0.0240 9.52 1.166 0.0327 0.0330 0.0342 0.0312 0.0325 11.03 1.252 0.0433 0.0437 0.0403 0.0445 0.0448 Tabulated from data in file CL00624.DAT & reduced using program Q02.00D Average Reynolds #: 100200 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -4.33 -0.236 0.0269 0.0281 0.0270 0.0270 0.0256 -2.80 -0.092 0.0212 0.0215 0.0199 0.0205 0.0229 -1.27 0.070 0.0163 0.0146 0.0157 0.0160 0.0191 0.24 0.321 0.0186 0.0182 0.0171 0.0213 0.0176 1.83 0.513 0.0191 0.0182 0.0202 0.0200 0.0181 3.37 0.663 0.0177 0.0170 0.0181 0.0178 0.0180 4.91 0.805 0.0173 0.0169 0.0174 0.0178 0.0170 6.43 0.939 0.0185 0.0173 0.0189 0.0192 0.0185 7.99 1.071 0.0234 0.0238 0.0240 0.0226 0.0231 9.50 1.161 0.0295 0.0298 0.0285 0.0294 0.0303 11.02 1.241 0.0368 0.0365 0.0345 0.0377 0.0386 Tabulated from data in file CL00626.DAT & reduced using program Q02.00D Average Reynolds #: 199100 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -4.24 -0.172 0.0203 0.0220 0.0203 0.0176 0.0213 -2.76 0.014 0.0150 0.0151 0.0152 0.0139 0.0159 -1.23 0.197 0.0119 0.0115 0.0124 0.0114 0.0124 0.31 0.349 0.0105 0.0108 0.0119 0.0090 0.0103 1.84 0.505 0.0107 0.0099 0.0122 0.0092 0.0116 3.38 0.664 0.0113 0.0110 0.0124 0.0100 0.0118 4.92 0.820 0.0122 0.0122 0.0123 0.0121 0.0122 6.45 0.961 0.0143 0.0138 0.0141 0.0147 0.0146 7.98 1.083 0.0185 0.0184 0.0182 0.0190 0.0186 9.52 1.187 0.0232 0.0215 0.0228 0.0236 0.0247 11.04 1.267 0.0285 0.0281 0.0272 0.0287 0.0300 Tabulated from data in file CL00628.DAT & reduced using program Q02.00D Average Reynolds #: 298900 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -4.89 -0.185 0.0212 0.0222 0.0231 0.0196 0.0198 -2.84 0.036 0.0123 0.0127 0.0132 0.0112 0.0121 -1.23 0.184 0.0096 0.0098 0.0100 0.0086 0.0102 0.30 0.340 0.0073 0.0071 0.0077 0.0069 0.0075 1.85 0.504 0.0078 0.0077 0.0085 0.0070 0.0081 3.39 0.664 0.0088 0.0086 0.0090 0.0084 0.0093 4.93 0.819 0.0105 0.0103 0.0105 0.0110 0.0103 6.40 0.952 0.0126 0.0125 0.0124 0.0128 0.0128 7.99 1.083 0.0166 0.0163 0.0162 0.0168 0.0172 9.52 1.199 0.0208 0.0199 0.0205 0.0210 0.0216 11.00 1.275 0.0250 0.0245 0.0258 0.0249 0.0250 Tabulated from data in file CL00630.DAT & reduced using program Q02.00D File 7037c.drg created on 09-12-1997 at 13:46:25 using program FORMAT