Airfoil: MA409 Builder: R. Conney Comment: clean Number of Reynolds #'s: 6 Average Reynolds #: 40700 Number of angles of attack: 7 alpha / Cl / Cd / Spanwise Cd's >>> -1.98 -0.007 0.0208 0.0170 0.0172 0.0310 0.0180 0.16 0.214 0.0162 0.0184 0.0158 0.0121 0.0183 2.11 0.421 0.0175 0.0137 0.0100 0.0263 0.0201 4.32 0.745 0.0199 0.0188 0.0200 0.0211 0.0195 6.35 0.905 0.0239 0.0212 0.0304 0.0250 0.0193 8.22 1.020 0.0276 0.0279 0.0324 0.0260 0.0241 10.34 1.091 0.0699 0.0837 0.1034 0.0416 0.0508 Tabulated from data in file MS00301.DAT & reduced using program Q01.00L Average Reynolds #: 60800 Number of angles of attack: 9 alpha / Cl / Cd / Spanwise Cd's >>> -2.71 -0.095 0.0240 0.0281 0.0243 0.0173 0.0261 -1.11 0.038 0.0137 0.0139 0.0114 0.0151 0.0143 0.56 0.198 0.0150 0.0066 0.0236 0.0202 0.0096 2.03 0.384 0.0170 0.0141 0.0158 0.0204 0.0175 3.26 0.575 0.0173 0.0128 0.0166 0.0207 0.0191 4.89 0.713 0.0147 0.0132 0.0128 0.0189 0.0140 6.36 0.835 0.0189 0.0204 0.0169 0.0195 0.0187 7.98 0.931 0.0289 0.0251 0.0307 0.0308 0.0289 9.58 1.012 0.0422 0.0287 0.0501 0.0499 0.0401 Tabulated from data in file MS00177.DAT & reduced using program Q01.00L Average Reynolds #: 101500 Number of angles of attack: 10 alpha / Cl / Cd / Spanwise Cd's >>> -4.39 -0.249 0.0264 0.0267 0.0233 0.0260 0.0296 -2.61 -0.104 0.0184 0.0189 0.0187 0.0177 0.0184 -1.24 0.020 0.0144 0.0142 0.0144 0.0135 0.0154 0.31 0.170 0.0105 0.0094 0.0113 0.0136 0.0078 1.81 0.413 0.0132 0.0115 0.0133 0.0151 0.0127 3.29 0.578 0.0138 0.0130 0.0127 0.0150 0.0145 5.07 0.733 0.0144 0.0136 0.0144 0.0157 0.0138 6.42 0.843 0.0181 0.0169 0.0173 0.0197 0.0186 8.24 0.954 0.0289 0.0242 0.0267 0.0322 0.0322 9.45 1.013 0.0395 0.0356 0.0372 0.0464 0.0389 Tabulated from data in file JG00179.DAT & reduced using program Q01.00L Average Reynolds #: 201900 Number of angles of attack: 10 alpha / Cl / Cd / Spanwise Cd's >>> -4.40 -0.245 0.0176 0.0161 0.0168 0.0200 0.0173 -2.83 -0.115 0.0143 0.0134 0.0144 0.0151 0.0145 -1.45 0.038 0.0111 0.0104 0.0103 0.0102 0.0133 -0.03 0.223 0.0089 0.0077 0.0093 0.0086 0.0100 1.72 0.411 0.0088 0.0080 0.0083 0.0107 0.0080 3.30 0.572 0.0096 0.0099 0.0091 0.0097 0.0096 4.71 0.703 0.0114 0.0114 0.0101 0.0119 0.0120 6.14 0.823 0.0151 0.0156 0.0139 0.0154 0.0156 7.58 0.925 0.0213 0.0193 0.0201 0.0226 0.0233 9.24 1.021 0.0343 0.0319 0.0323 0.0369 0.0361 Tabulated from data in file AB00181.DAT & reduced using program Q01.00L Average Reynolds #: 302500 Number of angles of attack: 10 alpha / Cl / Cd / Spanwise Cd's >>> -4.68 -0.273 0.0146 0.0137 0.0140 0.0163 0.0145 -3.14 -0.137 0.0141 0.0132 0.0122 0.0180 0.0132 -1.43 0.069 0.0085 0.0071 0.0089 0.0091 0.0087 -0.00 0.237 0.0078 0.0074 0.0076 0.0078 0.0085 1.61 0.403 0.0069 0.0071 0.0073 0.0063 0.0069 3.49 0.589 0.0086 0.0085 0.0084 0.0087 0.0089 4.78 0.703 0.0105 0.0104 0.0096 0.0110 0.0111 6.21 0.824 0.0138 0.0135 0.0130 0.0140 0.0146 8.00 0.960 0.0214 0.0192 0.0195 0.0233 0.0234 9.39 1.038 0.0321 0.0293 0.0300 0.0351 0.0340 Tabulated from data in file AB00183.DAT & reduced using program Q01.00L Average Reynolds #: 305400 Number of angles of attack: 1 alpha / Cl / Cd / Spanwise Cd's >>> -6.09 -0.438 0.0695 0.0702 0.0689 0.0710 0.0678 Tabulated from data in file AB00523.DAT & reduced using program Q01.00L File ma409.drg created on 12-05-1997 at 15:25:58 using program FORMAT