Airfoil: S7012 (B) Builder: M. Lachowski Comment: clean Number of Reynolds #'s: 5 Average Reynolds #: 61100 Number of angles of attack: 12 alpha / Cl / Cd / Spanwise Cd's >>> -5.80 -0.420 0.0400 0.0439 0.0399 0.0358 0.0405 -4.31 -0.299 0.0253 0.0309 0.0250 0.0225 0.0227 -2.78 -0.162 0.0169 0.0188 0.0142 0.0168 0.0178 -1.28 -0.035 0.0124 0.0186 0.0080 0.0142 0.0088 0.13 0.107 0.0109 0.0100 0.0109 0.0140 0.0086 1.75 0.388 0.0171 0.0124 0.0151 0.0283 0.0124 3.52 0.576 0.0230 0.0224 0.0291 0.0241 0.0161 4.85 0.692 0.0175 0.0144 0.0196 0.0206 0.0155 6.36 0.827 0.0224 0.0201 0.0191 0.0284 0.0219 7.89 0.953 0.0250 0.0236 0.0204 0.0311 0.0248 9.58 1.059 0.0351 0.0265 0.0329 0.0473 0.0339 10.99 1.103 0.0535 0.0371 0.0466 0.0683 0.0620 Tabulated from data in file AB00094.DAT & reduced using program Q01.00L Average Reynolds #: 101200 Number of angles of attack: 12 alpha / Cl / Cd / Spanwise Cd's >>> -5.86 -0.456 0.0355 0.0375 0.0317 0.0340 0.0390 -4.38 -0.322 0.0202 0.0195 0.0199 0.0196 0.0218 -2.88 -0.185 0.0143 0.0128 0.0126 0.0157 0.0162 -1.29 -0.048 0.0102 0.0105 0.0088 0.0099 0.0118 0.26 0.185 0.0118 0.0112 0.0124 0.0131 0.0104 1.79 0.369 0.0136 0.0130 0.0159 0.0144 0.0110 3.32 0.520 0.0151 0.0149 0.0169 0.0157 0.0129 4.79 0.669 0.0161 0.0163 0.0167 0.0162 0.0151 6.42 0.833 0.0171 0.0168 0.0163 0.0189 0.0164 7.98 0.966 0.0226 0.0218 0.0247 0.0230 0.0211 9.53 1.055 0.0377 0.0362 0.0387 0.0384 0.0375 11.03 1.106 0.0603 0.0583 0.0630 0.0627 0.0572 Tabulated from data in file AB00092.DAT & reduced using program Q01.00L Average Reynolds #: 152100 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -5.93 -0.435 0.0281 0.0269 0.0264 0.0298 0.0291 -4.13 -0.273 0.0167 0.0160 0.0160 0.0181 0.0168 -2.52 -0.125 0.0112 0.0106 0.0120 0.0119 0.0102 -1.10 0.027 0.0097 0.0093 0.0096 0.0107 0.0091 0.59 0.230 0.0095 0.0086 0.0098 0.0112 0.0083 1.99 0.375 0.0110 0.0108 0.0113 0.0118 0.0099 3.46 0.533 0.0123 0.0126 0.0121 0.0126 0.0120 5.17 0.713 0.0134 0.0139 0.0127 0.0139 0.0132 6.73 0.868 0.0157 0.0160 0.0148 0.0162 0.0159 8.07 0.965 0.0230 0.0240 0.0225 0.0222 0.0235 9.62 1.056 0.0349 0.0354 0.0350 0.0350 0.0344 Tabulated from data in file PG00565.DAT & reduced using program Q01.00L Average Reynolds #: 202200 Number of angles of attack: 12 alpha / Cl / Cd / Spanwise Cd's >>> -5.90 -0.437 0.0233 0.0221 0.0222 0.0247 0.0243 -4.39 -0.302 0.0160 0.0155 0.0155 0.0170 0.0160 -2.86 -0.154 0.0111 0.0100 0.0112 0.0127 0.0107 -1.38 0.007 0.0089 0.0083 0.0089 0.0099 0.0084 0.36 0.193 0.0075 0.0083 0.0068 0.0080 0.0068 1.78 0.347 0.0092 0.0095 0.0091 0.0094 0.0087 3.37 0.522 0.0105 0.0109 0.0105 0.0102 0.0103 4.78 0.671 0.0115 0.0117 0.0110 0.0118 0.0116 6.45 0.839 0.0135 0.0143 0.0125 0.0140 0.0132 7.95 0.958 0.0204 0.0209 0.0197 0.0200 0.0210 9.48 1.052 0.0313 0.0319 0.0320 0.0305 0.0306 10.99 1.097 0.0538 0.0546 0.0540 0.0528 0.0537 Tabulated from data in file AB00090.DAT & reduced using program Q01.00L Average Reynolds #: 303000 Number of angles of attack: 12 alpha / Cl / Cd / Spanwise Cd's >>> -5.83 -0.445 0.0202 0.0193 0.0187 0.0210 0.0216 -4.21 -0.291 0.0129 0.0126 0.0122 0.0142 0.0127 -2.75 -0.146 0.0099 0.0097 0.0089 0.0119 0.0089 -1.15 0.041 0.0076 0.0067 0.0078 0.0088 0.0073 0.15 0.163 0.0077 0.0068 0.0085 0.0082 0.0072 1.71 0.342 0.0075 0.0074 0.0078 0.0075 0.0075 3.33 0.526 0.0086 0.0088 0.0087 0.0083 0.0088 4.91 0.703 0.0097 0.0102 0.0092 0.0098 0.0097 6.51 0.862 0.0121 0.0124 0.0113 0.0122 0.0124 7.89 0.979 0.0181 0.0182 0.0175 0.0180 0.0186 9.60 1.086 0.0286 0.0294 0.0289 0.0283 0.0279 11.07 1.143 0.0549 0.0543 0.0582 0.0585 0.0488 Tabulated from data in file AB00088.DAT & reduced using program Q01.00L File s7012b.drg created on 12-05-1997 at 15:25:59 using program FORMAT