Airfoil: S7012 (B) Builder: M. Lachowski Comment: clean: flap = 5 degs Number of Reynolds #'s: 4 Average Reynolds #: 60300 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -4.84 -0.175 0.0217 0.0210 0.0200 0.0237 0.0222 -3.31 -0.039 0.0168 0.0153 0.0177 0.0157 0.0187 -1.80 0.073 0.0146 0.0148 0.0183 0.0128 0.0124 -0.25 0.237 0.0204 0.0172 0.0234 0.0197 0.0212 1.27 0.405 0.0263 0.0214 0.0242 0.0332 0.0263 2.85 0.646 0.0249 0.0220 0.0224 0.0331 0.0221 4.38 0.798 0.0303 0.0283 0.0261 0.0392 0.0275 5.93 0.921 0.0289 0.0287 0.0267 0.0269 0.0332 7.45 1.027 0.0287 0.0303 0.0244 0.0306 0.0294 8.97 1.111 0.0462 0.0523 0.0512 0.0418 0.0395 10.46 1.154 0.0663 0.0653 0.0765 0.0609 0.0625 Tabulated from data in file CL00856.DAT & reduced using program Q02.00D Average Reynolds #: 99900 Number of angles of attack: 10 alpha / Cl / Cd / Spanwise Cd's >>> -4.85 -0.122 0.0184 0.0192 0.0172 0.0192 0.0180 -3.31 -0.019 0.0144 0.0156 0.0150 0.0139 0.0132 -1.78 0.093 0.0137 0.0140 0.0134 0.0132 0.0142 -0.24 0.275 0.0138 0.0152 0.0107 0.0156 0.0136 1.33 0.552 0.0142 0.0121 0.0148 0.0153 0.0147 2.87 0.721 0.0145 0.0127 0.0134 0.0159 0.0161 4.40 0.858 0.0175 0.0167 0.0177 0.0177 0.0179 5.93 0.993 0.0202 0.0193 0.0182 0.0214 0.0221 7.46 1.080 0.0289 0.0306 0.0272 0.0284 0.0296 8.98 1.144 0.0430 0.0451 0.0402 0.0449 0.0418 Tabulated from data in file CL00858.DAT & reduced using program Q02.00D Average Reynolds #: 199800 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -6.86 -0.247 0.0200 0.0201 0.0177 0.0212 0.0209 -5.34 -0.097 0.0149 0.0158 0.0137 0.0147 0.0154 -3.77 0.057 0.0113 0.0111 0.0108 0.0125 0.0108 -2.25 0.202 0.0109 0.0107 0.0103 0.0120 0.0106 -0.72 0.351 0.0118 0.0116 0.0117 0.0148 0.0090 0.82 0.504 0.0106 0.0106 0.0124 0.0115 0.0081 2.34 0.662 0.0105 0.0105 0.0107 0.0103 0.0106 3.90 0.841 0.0131 0.0135 0.0129 0.0134 0.0125 5.42 0.985 0.0156 0.0159 0.0160 0.0152 0.0156 6.95 1.084 0.0222 0.0220 0.0229 0.0219 0.0219 8.47 1.158 0.0326 0.0327 0.0337 0.0318 0.0324 Tabulated from data in file CL00860.DAT & reduced using program Q02.00D Average Reynolds #: 299900 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -6.87 -0.257 0.0185 0.0188 0.0166 0.0205 0.0182 -5.33 -0.104 0.0133 0.0134 0.0128 0.0153 0.0118 -3.81 0.047 0.0100 0.0102 0.0100 0.0103 0.0097 -2.26 0.199 0.0088 0.0089 0.0091 0.0088 0.0084 -0.72 0.384 0.0086 0.0093 0.0084 0.0082 0.0085 0.85 0.539 0.0079 0.0075 0.0078 0.0079 0.0084 2.34 0.691 0.0094 0.0093 0.0094 0.0092 0.0095 3.75 0.835 0.0111 0.0111 0.0114 0.0111 0.0110 5.43 0.990 0.0139 0.0137 0.0141 0.0138 0.0140 6.96 1.099 0.0200 0.0199 0.0208 0.0195 0.0196 8.46 1.174 0.0297 0.0301 0.0301 0.0294 0.0293 Tabulated from data in file CL00862.DAT & reduced using program Q02.00D File s7012bf5.drg created on 09-12-1997 at 13:46:25 using program FORMAT