Airfoil: S7075 (A) Builder: J. Robertson Comment: plain trip @ x/c = 68% (h/c = 0.17%; w/c = 2.0%) Number of Reynolds #'s: 4 Average Reynolds #: 99800 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -4.00 -0.188 0.0264 0.0260 0.0267 0.0277 0.0252 -2.49 -0.040 0.0192 0.0202 0.0185 0.0197 0.0182 -0.94 0.083 0.0147 0.0140 0.0137 0.0156 0.0156 0.62 0.291 0.0173 0.0159 0.0170 0.0192 0.0172 2.15 0.518 0.0216 0.0219 0.0219 0.0226 0.0202 3.71 0.715 0.0175 0.0164 0.0176 0.0183 0.0177 5.24 0.851 0.0165 0.0150 0.0178 0.0162 0.0170 6.77 0.971 0.0191 0.0188 0.0190 0.0198 0.0189 8.29 1.092 0.0243 0.0221 0.0261 0.0244 0.0245 9.81 1.147 0.0334 0.0317 0.0329 0.0340 0.0348 11.33 1.198 0.0478 0.0474 0.0460 0.0478 0.0501 Tabulated from data in file CL00700.DAT & reduced using program Q02.00D Average Reynolds #: 199100 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -3.80 -0.034 0.0161 0.0150 0.0158 0.0179 0.0157 -2.42 0.098 0.0128 0.0136 0.0120 0.0127 0.0129 -0.90 0.250 0.0103 0.0105 0.0104 0.0106 0.0098 0.64 0.385 0.0116 0.0114 0.0115 0.0115 0.0121 2.02 0.535 0.0107 0.0103 0.0108 0.0107 0.0112 3.73 0.727 0.0100 0.0097 0.0102 0.0101 0.0100 5.13 0.853 0.0124 0.0126 0.0125 0.0122 0.0125 6.78 0.988 0.0157 0.0153 0.0157 0.0157 0.0161 8.31 1.095 0.0205 0.0193 0.0203 0.0206 0.0217 9.82 1.167 0.0286 0.0286 0.0280 0.0288 0.0291 11.34 1.220 0.0404 0.0420 0.0391 0.0393 0.0413 Tabulated from data in file CL00702.DAT & reduced using program Q02.00D Average Reynolds #: 202900 Number of angles of attack: 1 alpha / Cl / Cd / Spanwise Cd's >>> -4.99 -0.144 0.0231 0.0216 0.0226 0.0249 0.0233 Tabulated from data in file CL00703.DAT & reduced using program Q02.00D Average Reynolds #: 300000 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -5.00 -0.154 0.0204 0.0195 0.0196 0.0229 0.0198 -3.46 -0.013 0.0129 0.0128 0.0123 0.0144 0.0121 -1.92 0.130 0.0102 0.0097 0.0104 0.0106 0.0100 -0.49 0.272 0.0086 0.0083 0.0090 0.0089 0.0083 1.14 0.468 0.0077 0.0071 0.0077 0.0078 0.0080 2.79 0.645 0.0081 0.0076 0.0086 0.0076 0.0086 4.24 0.785 0.0097 0.0095 0.0101 0.0095 0.0099 5.77 0.918 0.0121 0.0118 0.0122 0.0122 0.0123 7.29 1.043 0.0157 0.0154 0.0155 0.0157 0.0160 8.83 1.144 0.0203 0.0194 0.0203 0.0204 0.0212 10.36 1.216 0.0287 0.0290 0.0281 0.0286 0.0291 Tabulated from data in file CL00705.DAT & reduced using program Q02.00D File 7075at1.drg created on 09-12-1997 at 13:46:25 using program FORMAT