Airfoil: GM15 Builder: G. Morris Comment: reflexed (flap = -8.5 degs) Number of Reynolds #'s: 4 Average Reynolds #: 60700 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -1.91 -0.341 0.0587 0.0789 0.0505 0.0420 0.0636 -0.29 -0.170 0.0286 0.0305 0.0243 0.0242 0.0354 1.20 -0.026 0.0183 0.0193 0.0185 0.0176 0.0178 2.50 0.112 0.0135 0.0137 0.0136 0.0133 0.0133 4.18 0.321 0.0127 0.0104 0.0115 0.0138 0.0150 5.60 0.464 0.0144 0.0131 0.0133 0.0152 0.0162 7.26 0.636 0.0191 0.0169 0.0180 0.0215 0.0202 8.75 0.773 0.0214 0.0193 0.0199 0.0247 0.0217 10.36 0.879 0.0237 0.0190 0.0241 0.0277 0.0242 11.81 0.994 0.0249 0.0239 0.0281 0.0273 0.0204 13.44 1.085 0.0343 0.0282 0.0342 0.0432 0.0317 Tabulated from data in file MS00409.DAT & reduced using program Q01.00L Average Reynolds #: 101300 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -1.93 -0.336 0.0471 0.0498 0.0546 0.0409 0.0433 -0.14 -0.151 0.0195 0.0191 0.0198 0.0189 0.0200 1.31 -0.020 0.0143 0.0140 0.0144 0.0152 0.0137 2.70 0.136 0.0115 0.0121 0.0121 0.0115 0.0104 4.19 0.285 0.0128 0.0124 0.0145 0.0128 0.0113 5.63 0.431 0.0154 0.0140 0.0157 0.0173 0.0144 7.27 0.591 0.0179 0.0168 0.0170 0.0184 0.0193 8.72 0.738 0.0176 0.0170 0.0174 0.0183 0.0179 10.42 0.897 0.0191 0.0187 0.0193 0.0197 0.0189 11.84 0.996 0.0294 0.0272 0.0295 0.0313 0.0296 13.45 1.088 0.0465 0.0433 0.0442 0.0507 0.0479 Tabulated from data in file JG00407.DAT & reduced using program Q01.00L Average Reynolds #: 202200 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -1.73 -0.276 0.0299 0.0293 0.0317 0.0295 0.0292 0.09 -0.088 0.0151 0.0151 0.0149 0.0163 0.0141 1.47 -0.002 0.0132 0.0123 0.0138 0.0145 0.0120 3.07 0.163 0.0117 0.0115 0.0122 0.0116 0.0113 4.53 0.309 0.0115 0.0108 0.0122 0.0113 0.0117 5.93 0.482 0.0115 0.0116 0.0112 0.0113 0.0118 7.46 0.644 0.0117 0.0122 0.0107 0.0119 0.0122 9.09 0.805 0.0136 0.0136 0.0125 0.0140 0.0143 10.64 0.937 0.0205 0.0197 0.0196 0.0212 0.0214 11.96 1.034 0.0283 0.0277 0.0271 0.0290 0.0292 13.53 1.109 0.0482 0.0498 0.0434 0.0516 0.0481 Tabulated from data in file MS00412.DAT & reduced using program Q01.00L Average Reynolds #: 302500 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -1.99 -0.301 0.0413 0.0406 0.0420 0.0417 0.0407 -0.49 -0.147 0.0165 0.0164 0.0150 0.0196 0.0151 2.04 0.055 0.0120 0.0116 0.0119 0.0133 0.0111 3.01 0.184 0.0110 0.0109 0.0116 0.0114 0.0100 4.54 0.343 0.0096 0.0088 0.0095 0.0102 0.0098 6.09 0.509 0.0093 0.0089 0.0094 0.0094 0.0096 7.54 0.655 0.0100 0.0101 0.0094 0.0100 0.0104 9.00 0.798 0.0118 0.0117 0.0112 0.0123 0.0120 10.51 0.928 0.0175 0.0167 0.0166 0.0186 0.0182 12.41 1.072 0.0294 0.0277 0.0281 0.0319 0.0299 13.77 1.133 0.0585 0.0578 0.0443 0.0665 0.0653 Tabulated from data in file MS00414.DAT & reduced using program Q01.00L File gm15f1.drg created on 12-05-1997 at 15:25:58 using program FORMAT