Airfoil: S7075 (A) Builder: J. Robertson Comment: Zig-Zag trip type "D" @ x/c = 68% (h/c = 0.25%) Number of Reynolds #'s: 4 Average Reynolds #: 60200 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -4.00 -0.190 0.0309 0.0319 0.0328 0.0296 0.0294 -2.49 -0.055 0.0236 0.0243 0.0241 0.0238 0.0222 -0.97 0.072 0.0183 0.0164 0.0193 0.0198 0.0177 0.58 0.238 0.0220 0.0229 0.0179 0.0243 0.0229 2.13 0.422 0.0241 0.0231 0.0250 0.0255 0.0227 3.72 0.680 0.0297 0.0285 0.0331 0.0292 0.0281 5.24 0.857 0.0228 0.0196 0.0268 0.0246 0.0203 6.73 0.970 0.0224 0.0225 0.0238 0.0211 0.0224 8.28 1.063 0.0315 0.0299 0.0255 0.0334 0.0373 9.82 1.136 0.0375 0.0381 0.0330 0.0376 0.0415 11.33 1.197 0.0573 0.0552 0.0522 0.0581 0.0636 Tabulated from data in file CL00707.DAT & reduced using program Q02.00D Average Reynolds #: 100200 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -5.00 -0.172 0.0292 0.0292 0.0277 0.0316 0.0284 -3.47 -0.027 0.0200 0.0193 0.0196 0.0216 0.0193 -1.95 0.107 0.0143 0.0138 0.0146 0.0147 0.0139 -0.50 0.207 0.0157 0.0150 0.0159 0.0166 0.0152 1.12 0.361 0.0194 0.0188 0.0192 0.0209 0.0189 2.55 0.571 0.0212 0.0218 0.0220 0.0209 0.0201 4.21 0.762 0.0169 0.0169 0.0177 0.0165 0.0165 5.76 0.896 0.0177 0.0172 0.0178 0.0179 0.0179 7.28 1.019 0.0209 0.0190 0.0208 0.0219 0.0220 8.80 1.109 0.0281 0.0291 0.0263 0.0281 0.0288 10.32 1.168 0.0389 0.0388 0.0379 0.0390 0.0396 Tabulated from data in file CL00709.DAT & reduced using program Q02.00D Average Reynolds #: 199600 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -4.97 -0.158 0.0236 0.0234 0.0228 0.0255 0.0227 -3.47 -0.028 0.0155 0.0157 0.0150 0.0163 0.0152 -1.94 0.121 0.0110 0.0112 0.0110 0.0110 0.0108 -0.41 0.265 0.0083 0.0085 0.0080 0.0082 0.0087 1.14 0.429 0.0090 0.0088 0.0090 0.0088 0.0094 2.68 0.605 0.0105 0.0100 0.0107 0.0105 0.0107 4.23 0.779 0.0109 0.0108 0.0111 0.0108 0.0110 5.77 0.908 0.0142 0.0140 0.0141 0.0141 0.0147 7.28 1.030 0.0174 0.0170 0.0171 0.0176 0.0180 8.81 1.118 0.0230 0.0215 0.0230 0.0236 0.0238 10.33 1.184 0.0320 0.0320 0.0311 0.0323 0.0324 Tabulated from data in file CL00711.DAT & reduced using program Q02.00D Average Reynolds #: 299700 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -5.00 -0.162 0.0217 0.0213 0.0207 0.0238 0.0211 -3.45 -0.023 0.0137 0.0139 0.0131 0.0144 0.0134 -1.89 0.124 0.0101 0.0100 0.0099 0.0104 0.0100 -0.40 0.259 0.0078 0.0078 0.0078 0.0080 0.0077 1.15 0.458 0.0077 0.0078 0.0079 0.0075 0.0077 2.68 0.626 0.0080 0.0081 0.0083 0.0071 0.0084 4.24 0.780 0.0103 0.0102 0.0106 0.0100 0.0103 5.76 0.917 0.0128 0.0124 0.0128 0.0131 0.0128 7.31 1.040 0.0161 0.0156 0.0160 0.0163 0.0166 8.83 1.140 0.0208 0.0196 0.0210 0.0212 0.0214 10.20 1.205 0.0277 0.0275 0.0275 0.0279 0.0277 Tabulated from data in file CL00713.DAT & reduced using program Q02.00D File 7075at2.drg created on 09-12-1997 at 13:46:25 using program FORMAT