Airfoil: A18 Builder: R. Cooney Comment: clean Number of Reynolds #'s: 7 Average Reynolds #: 40000 Number of angles of attack: 7 alpha / Cl / Cd / Spanwise Cd's >>> -1.16 0.117 0.0244 0.0247 0.0203 0.0290 0.0236 0.93 0.324 0.0202 0.0155 0.0237 0.0253 0.0164 2.82 0.540 0.0349 0.0363 0.0353 0.0396 0.0286 5.05 0.842 0.0405 0.0350 0.0401 0.0471 0.0397 7.04 1.007 0.0314 0.0316 0.0402 0.0284 0.0256 9.08 1.108 0.0283 0.0254 0.0371 0.0270 0.0237 11.10 1.155 0.0572 0.0516 0.0734 0.0510 0.0525 Tabulated from data in file MS00278.DAT & reduced using program Q01.00L Average Reynolds #: 60700 Number of angles of attack: 9 alpha / Cl / Cd / Spanwise Cd's >>> -2.07 0.027 0.0229 0.0231 0.0228 0.0217 0.0240 -0.17 0.216 0.0182 0.0168 0.0184 0.0206 0.0170 1.14 0.407 0.0201 0.0152 0.0217 0.0241 0.0194 2.44 0.591 0.0214 0.0151 0.0222 0.0276 0.0208 4.17 0.810 0.0231 0.0202 0.0240 0.0249 0.0233 6.02 0.967 0.0207 0.0189 0.0244 0.0249 0.0147 7.62 1.057 0.0243 0.0222 0.0196 0.0334 0.0221 9.15 1.141 0.0318 0.0253 0.0298 0.0395 0.0325 10.41 1.186 0.0395 0.0331 0.0414 0.0493 0.0343 Tabulated from data in file JG00161.DAT & reduced using program Q01.00L Average Reynolds #: 100700 Number of angles of attack: 9 alpha / Cl / Cd / Spanwise Cd's >>> -1.53 0.084 0.0183 0.0159 0.0201 0.0172 0.0201 -0.37 0.266 0.0141 0.0137 0.0148 0.0136 0.0142 1.10 0.468 0.0147 0.0143 0.0165 0.0145 0.0136 2.82 0.653 0.0161 0.0147 0.0176 0.0162 0.0158 4.38 0.787 0.0153 0.0152 0.0168 0.0139 0.0152 5.94 0.920 0.0165 0.0174 0.0162 0.0164 0.0161 7.60 1.024 0.0240 0.0225 0.0245 0.0250 0.0239 9.01 1.105 0.0300 0.0304 0.0309 0.0309 0.0280 10.18 1.145 0.0366 0.0330 0.0426 0.0378 0.0330 Tabulated from data in file MS00163.DAT & reduced using program Q01.00L Average Reynolds #: 201800 Number of angles of attack: 9 alpha / Cl / Cd / Spanwise Cd's >>> -1.55 0.199 0.0126 0.0123 0.0142 0.0115 0.0124 0.17 0.385 0.0093 0.0092 0.0102 0.0091 0.0088 1.53 0.525 0.0089 0.0078 0.0102 0.0088 0.0089 2.93 0.673 0.0100 0.0083 0.0102 0.0104 0.0109 4.38 0.809 0.0117 0.0123 0.0099 0.0121 0.0125 5.59 0.906 0.0140 0.0156 0.0125 0.0139 0.0140 7.50 1.045 0.0196 0.0203 0.0188 0.0201 0.0192 8.93 1.135 0.0249 0.0256 0.0256 0.0237 0.0247 10.22 1.191 0.0316 0.0314 0.0339 0.0307 0.0304 Tabulated from data in file MS00165.DAT & reduced using program Q01.00L Average Reynolds #: 204500 Number of angles of attack: 2 alpha / Cl / Cd / Spanwise Cd's >>> -5.29 -0.375 0.0685 0.0706 0.0697 0.0687 0.0649 -3.39 -0.093 0.0178 0.0182 0.0185 0.0169 0.0175 Tabulated from data in file AB00521.DAT & reduced using program Q01.00L Average Reynolds #: 300400 Number of angles of attack: 9 alpha / Cl / Cd / Spanwise Cd's >>> -2.37 0.122 0.0108 0.0111 0.0115 0.0103 0.0103 -0.45 0.327 0.0100 0.0096 0.0109 0.0096 0.0098 0.94 0.474 0.0080 0.0079 0.0081 0.0080 0.0079 2.39 0.622 0.0082 0.0077 0.0081 0.0084 0.0088 4.28 0.792 0.0099 0.0114 0.0088 0.0097 0.0098 5.81 0.914 0.0139 0.0146 0.0133 0.0140 0.0138 7.94 1.077 0.0194 0.0198 0.0187 0.0194 0.0196 9.31 1.156 0.0234 0.0235 0.0242 0.0226 0.0234 10.27 1.192 0.0295 0.0275 0.0307 0.0309 0.0289 Tabulated from data in file MS00167.DAT & reduced using program Q01.00L Average Reynolds #: 305600 Number of angles of attack: 2 alpha / Cl / Cd / Spanwise Cd's >>> -5.35 -0.332 0.0623 0.0619 0.0644 0.0716 0.0514 -3.58 -0.057 0.0137 0.0147 0.0138 0.0128 0.0137 Tabulated from data in file AB00522.DAT & reduced using program Q01.00L File a18.drg created on 12-05-1997 at 15:25:58 using program FORMAT