Airfoil: S7075 (A) Builder: J. Robertson Comment: flap = 10 degs: Zig-Zag trip type "D" @ x/c = 68% (h/c = 0.25%) Number of Reynolds #'s: 4 Average Reynolds #: 60300 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -5.99 -0.018 0.0385 0.0378 0.0378 0.0368 0.0414 -4.43 0.161 0.0325 0.0325 0.0308 0.0325 0.0342 -2.94 0.274 0.0289 0.0291 0.0284 0.0280 0.0301 -1.40 0.409 0.0305 0.0301 0.0298 0.0326 0.0296 0.13 0.551 0.0350 0.0347 0.0325 0.0353 0.0375 1.66 0.661 0.0375 0.0403 0.0298 0.0326 0.0472 3.21 0.880 0.0455 0.0445 0.0472 0.0457 0.0446 4.80 1.185 0.0281 0.0267 0.0313 0.0242 0.0303 6.31 1.245 0.0373 0.0341 0.0381 0.0392 0.0377 7.82 1.283 0.0445 0.0436 0.0447 0.0456 0.0441 9.33 1.338 0.0593 0.0627 0.0580 0.0568 0.0596 Tabulated from data in file CL00744.DAT & reduced using program Q02.00D Average Reynolds #: 99600 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -6.00 -0.014 0.0336 0.0336 0.0331 0.0348 0.0330 -4.46 0.151 0.0286 0.0282 0.0292 0.0291 0.0278 -2.92 0.295 0.0265 0.0268 0.0270 0.0257 0.0266 -1.40 0.426 0.0267 0.0273 0.0253 0.0279 0.0265 0.15 0.578 0.0326 0.0293 0.0356 0.0363 0.0292 1.67 0.679 0.0399 0.0398 0.0396 0.0405 0.0397 3.25 1.044 0.0306 0.0292 0.0301 0.0322 0.0307 4.79 1.191 0.0249 0.0257 0.0236 0.0243 0.0258 6.32 1.265 0.0313 0.0311 0.0309 0.0315 0.0317 7.82 1.294 0.0403 0.0411 0.0389 0.0407 0.0405 9.34 1.345 0.0511 0.0527 0.0496 0.0511 0.0510 Tabulated from data in file CL00746.DAT & reduced using program Q02.00D Average Reynolds #: 198500 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -5.92 0.241 0.0181 0.0183 0.0177 0.0189 0.0177 -4.35 0.383 0.0144 0.0144 0.0145 0.0145 0.0144 -2.88 0.525 0.0139 0.0139 0.0135 0.0138 0.0142 -1.25 0.675 0.0144 0.0140 0.0139 0.0144 0.0151 0.21 0.813 0.0150 0.0148 0.0149 0.0150 0.0154 1.74 0.976 0.0168 0.0165 0.0168 0.0167 0.0171 3.26 1.161 0.0160 0.0159 0.0161 0.0158 0.0163 4.76 1.203 0.0230 0.0227 0.0223 0.0233 0.0238 6.31 1.266 0.0285 0.0282 0.0277 0.0289 0.0291 7.81 1.323 0.0353 0.0349 0.0349 0.0350 0.0363 9.34 1.387 0.0444 0.0454 0.0436 0.0439 0.0448 Tabulated from data in file CL00748.DAT & reduced using program Q02.00D Average Reynolds #: 297900 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -7.15 0.107 0.0223 0.0219 0.0212 0.0241 0.0219 -4.38 0.403 0.0130 0.0129 0.0128 0.0132 0.0131 -2.85 0.563 0.0121 0.0120 0.0119 0.0120 0.0124 -1.34 0.711 0.0129 0.0127 0.0126 0.0129 0.0133 0.19 0.861 0.0128 0.0125 0.0128 0.0129 0.0131 1.74 1.014 0.0129 0.0127 0.0128 0.0129 0.0134 3.26 1.127 0.0166 0.0163 0.0163 0.0169 0.0169 4.77 1.168 0.0231 0.0226 0.0223 0.0235 0.0239 6.32 1.243 0.0278 0.0276 0.0268 0.0286 0.0283 7.86 1.324 0.0335 0.0336 0.0330 0.0331 0.0344 9.33 1.389 0.0414 0.0430 0.0403 0.0408 0.0413 Tabulated from data in file CL00750.DAT & reduced using program Q02.00D File 7075atf1.drg created on 09-12-1997 at 13:46:25 using program FORMAT