Airfoil: NACA 6409 Builder: H. Halsey Comment: clean Number of Reynolds #'s: 3 Average Reynolds #: 61000 Number of angles of attack: 6 alpha / Cl / Cd / Spanwise Cd's >>> -2.80 -0.004 0.0623 0.0661 0.0483 0.0602 0.0744 -1.13 0.238 0.0373 0.0368 0.0340 0.0404 0.0379 0.26 0.452 0.0363 0.0367 0.0368 0.0370 0.0350 2.09 0.650 0.0367 0.0355 0.0349 0.0394 0.0370 3.33 0.774 0.0399 0.0376 0.0411 0.0410 0.0400 5.00 0.923 0.0468 0.0388 0.0494 0.0518 0.0470 Tabulated from data in file AB00187.DAT & reduced using program Q01.00L Average Reynolds #: 100700 Number of angles of attack: 9 alpha / Cl / Cd / Spanwise Cd's >>> -2.68 0.194 0.0378 0.0371 0.0356 0.0404 0.0383 -1.00 0.433 0.0228 0.0188 0.0259 0.0269 0.0195 0.26 0.563 0.0200 0.0184 0.0233 0.0235 0.0148 1.98 0.728 0.0188 0.0166 0.0236 0.0219 0.0132 3.34 0.861 0.0197 0.0175 0.0219 0.0220 0.0173 5.09 1.017 0.0213 0.0193 0.0226 0.0240 0.0193 6.47 1.145 0.0219 0.0222 0.0225 0.0237 0.0191 8.12 1.285 0.0227 0.0248 0.0218 0.0243 0.0199 9.73 1.410 0.0252 0.0249 0.0270 0.0256 0.0231 Tabulated from data in file AB00189.DAT & reduced using program Q01.00L Average Reynolds #: 200600 Number of angles of attack: 10 alpha / Cl / Cd / Spanwise Cd's >>> -2.89 0.282 0.0186 0.0132 0.0190 0.0232 0.0191 -1.37 0.435 0.0143 0.0117 0.0158 0.0167 0.0128 0.22 0.601 0.0136 0.0113 0.0159 0.0156 0.0116 1.67 0.745 0.0125 0.0115 0.0138 0.0143 0.0103 3.34 0.908 0.0134 0.0128 0.0135 0.0153 0.0122 4.97 1.070 0.0142 0.0136 0.0146 0.0159 0.0129 6.97 1.258 0.0160 0.0165 0.0153 0.0163 0.0159 8.11 1.352 0.0174 0.0175 0.0166 0.0183 0.0173 10.13 1.457 0.0211 0.0226 0.0204 0.0202 0.0211 11.33 1.440 0.0277 0.0251 0.0310 0.0235 0.0313 Tabulated from data in file AB00191.DAT & reduced using program Q01.00L File n6409.drg created on 12-05-1997 at 15:25:59 using program FORMAT