Airfoil: SD7037 (E) Builder: J. Robertson Comment: clean, LE flap = -3 degs, TE flap = -2.5 degs Number of Reynolds #'s: 3 Average Reynolds #: 105616 Number of angles of attack: 18 alpha / Cl / Cd / Spanwise Cd's >>> -6.16 -0.415 0.0410 0.0416 0.0427 0.0395 0.0403 -5.19 -0.346 0.0278 0.0278 0.0280 0.0274 0.0283 -4.11 -0.266 0.0212 0.0207 0.0218 0.0212 0.0211 -2.96 -0.176 0.0161 0.0155 0.0163 0.0161 0.0162 -2.12 -0.099 0.0144 0.0136 0.0142 0.0140 0.0159 -1.07 0.037 0.0130 0.0132 0.0117 0.0132 0.0138 0.01 0.228 0.0134 0.0135 0.0131 0.0132 0.0138 1.02 0.355 0.0137 0.0144 0.0137 0.0133 0.0135 2.01 0.448 0.0144 0.0153 0.0143 0.0137 0.0142 3.03 0.539 0.0154 0.0162 0.0159 0.0142 0.0151 4.13 0.641 0.0158 0.0170 0.0158 0.0154 0.0150 5.15 0.730 0.0163 0.0171 0.0168 0.0156 0.0156 6.13 0.820 0.0175 0.0184 0.0173 0.0173 0.0169 7.16 0.898 0.0207 0.0205 0.0214 0.0199 0.0211 8.21 0.976 0.0250 0.0258 0.0273 0.0231 0.0239 9.20 1.037 0.0310 0.0333 0.0298 0.0288 0.0321 10.22 1.086 0.0385 0.0415 0.0378 0.0367 0.0379 11.21 1.121 0.0507 0.0509 0.0482 0.0504 0.0534 Tabulated from data in file cl02323.dat & reduced using program C06.01 Average Reynolds #: 200149 Number of angles of attack: 19 alpha / Cl / Cd / Spanwise Cd's >>> -6.06 -0.429 0.0363 0.0368 0.0350 0.0354 0.0382 -4.83 -0.331 0.0209 0.0207 0.0207 0.0202 0.0220 -4.12 -0.272 0.0174 0.0177 0.0166 0.0175 0.0179 -2.94 -0.115 0.0129 0.0129 0.0117 0.0137 0.0132 -2.04 -0.002 0.0113 0.0136 0.0099 0.0110 0.0107 -1.04 0.103 0.0102 0.0112 0.0092 0.0111 0.0092 0.14 0.217 0.0097 0.0103 0.0091 0.0101 0.0092 1.00 0.309 0.0099 0.0105 0.0099 0.0098 0.0095 2.10 0.419 0.0099 0.0105 0.0101 0.0093 0.0097 3.07 0.524 0.0105 0.0106 0.0108 0.0106 0.0101 4.08 0.625 0.0113 0.0111 0.0116 0.0115 0.0108 5.10 0.728 0.0121 0.0121 0.0124 0.0121 0.0117 6.41 0.846 0.0149 0.0154 0.0147 0.0144 0.0150 7.22 0.916 0.0175 0.0178 0.0175 0.0173 0.0175 8.24 0.998 0.0209 0.0211 0.0210 0.0208 0.0206 9.16 1.062 0.0237 0.0241 0.0242 0.0233 0.0231 10.33 1.131 0.0297 0.0296 0.0293 0.0306 0.0293 11.19 1.170 0.0355 0.0344 0.0356 0.0366 0.0353 12.21 1.193 0.0454 0.0408 0.0451 0.0514 0.0444 Tabulated from data in file cl02315.dat & reduced using program C06.01 Average Reynolds #: 299430 Number of angles of attack: 20 alpha / Cl / Cd / Spanwise Cd's >>> -6.33 -0.460 0.0498 0.0510 0.0487 0.0477 0.0516 -5.40 -0.382 0.0248 0.0249 0.0245 0.0241 0.0255 -3.97 -0.224 0.0158 0.0142 0.0170 0.0175 0.0146 -3.07 -0.108 0.0110 0.0113 0.0108 0.0120 0.0099 -2.28 -0.021 0.0096 0.0095 0.0098 0.0103 0.0087 -1.11 0.096 0.0096 0.0100 0.0091 0.0100 0.0095 -0.10 0.200 0.0097 0.0102 0.0094 0.0100 0.0092 0.93 0.310 0.0092 0.0095 0.0090 0.0088 0.0093 1.87 0.405 0.0090 0.0093 0.0088 0.0089 0.0089 2.89 0.514 0.0087 0.0088 0.0086 0.0089 0.0085 3.92 0.623 0.0096 0.0096 0.0097 0.0096 0.0092 4.92 0.723 0.0106 0.0105 0.0110 0.0107 0.0102 5.92 0.817 0.0125 0.0123 0.0127 0.0124 0.0125 7.02 0.917 0.0151 0.0150 0.0154 0.0151 0.0150 7.97 1.003 0.0173 0.0174 0.0174 0.0172 0.0172 8.98 1.085 0.0197 0.0197 0.0201 0.0207 0.0183 9.97 1.151 0.0235 0.0227 0.0238 0.0243 0.0233 11.06 1.206 0.0295 0.0276 0.0301 0.0308 0.0294 12.06 1.233 0.0382 0.0334 0.0374 0.0434 0.0386 13.02 1.233 0.0583 0.0362 0.0460 0.0791 0.0718 Tabulated from data in file cl02313.dat & reduced using program C06.01 File 7037ef1.drg created using program C06.01 on Mon Feb 02 15:11:43 1998