Airfoil: BW-3 Builder: M. Allen Comment: Zig-Zag trip type "C" @ u.s. x/c = 2% & l.s. x/c = 5% (h = 0.023") Number of Reynolds #'s: 5 Average Reynolds #: 99700 Number of angles of attack: 9 alpha / Cl / Cd / Spanwise Cd's >>> -2.14 -0.153 0.0732 0.0772 0.0695 0.0669 0.0790 -0.46 0.182 0.0400 0.0392 0.0403 0.0421 0.0384 1.14 0.520 0.0265 0.0266 0.0258 0.0267 0.0271 2.59 0.666 0.0255 0.0254 0.0244 0.0262 0.0260 4.09 0.811 0.0250 0.0254 0.0246 0.0246 0.0253 5.68 0.949 0.0270 0.0263 0.0268 0.0276 0.0275 7.19 1.071 0.0311 0.0304 0.0311 0.0312 0.0317 8.76 1.191 0.0366 0.0359 0.0362 0.0362 0.0383 10.29 1.293 0.0479 0.0469 0.0466 0.0479 0.0500 Tabulated from data in file PG01773.DAT & reduced using program Q05.01D Average Reynolds #: 199200 Number of angles of attack: 10 alpha / Cl / Cd / Spanwise Cd's >>> -3.64 -0.286 0.0820 0.0887 0.0768 0.0738 0.0887 -2.11 0.024 0.0477 0.0498 0.0453 0.0440 0.0516 -0.63 0.261 0.0306 0.0329 0.0282 0.0277 0.0335 1.26 0.565 0.0219 0.0233 0.0209 0.0212 0.0221 2.76 0.733 0.0216 0.0216 0.0215 0.0214 0.0218 4.33 0.882 0.0236 0.0229 0.0233 0.0240 0.0242 5.80 1.007 0.0275 0.0263 0.0276 0.0276 0.0283 7.34 1.130 0.0324 0.0316 0.0321 0.0330 0.0329 8.87 1.243 0.0398 0.0388 0.0397 0.0416 0.0392 10.25 1.344 0.0550 0.0537 0.0555 0.0573 0.0536 Tabulated from data in file PG01775.DAT & reduced using program Q05.01D Average Reynolds #: 298300 Number of angles of attack: 10 alpha / Cl / Cd / Spanwise Cd's >>> -3.59 -0.180 0.0704 0.0784 0.0684 0.0656 0.0693 -2.07 0.060 0.0484 0.0531 0.0460 0.0446 0.0500 -0.49 0.365 0.0297 0.0303 0.0299 0.0300 0.0288 1.08 0.586 0.0196 0.0203 0.0193 0.0193 0.0196 2.63 0.747 0.0202 0.0201 0.0201 0.0200 0.0205 4.13 0.890 0.0221 0.0218 0.0218 0.0223 0.0226 5.66 1.026 0.0256 0.0250 0.0253 0.0257 0.0265 7.28 1.156 0.0314 0.0300 0.0316 0.0315 0.0326 8.93 1.268 0.0396 0.0378 0.0389 0.0409 0.0409 10.42 1.361 0.0505 0.0491 0.0486 0.0543 0.0500 Tabulated from data in file PG01777.DAT & reduced using program Q05.01D Average Reynolds #: 402400 Number of angles of attack: 2 alpha / Cl / Cd / Spanwise Cd's >>> -3.60 -0.182 0.0687 0.0754 0.0679 0.0630 0.0684 -2.06 0.143 0.0441 0.0464 0.0422 0.0413 0.0464 Tabulated from data in file PG01779.DAT & reduced using program Q05.01D Average Reynolds #: 397200 Number of angles of attack: 7 alpha / Cl / Cd / Spanwise Cd's >>> -0.52 0.409 0.0251 0.0267 0.0253 0.0235 0.0249 0.92 0.597 0.0186 0.0187 0.0184 0.0186 0.0188 2.50 0.765 0.0195 0.0193 0.0195 0.0194 0.0198 4.33 0.941 0.0221 0.0219 0.0219 0.0225 0.0221 6.00 1.087 0.0259 0.0252 0.0254 0.0262 0.0268 7.64 1.209 0.0314 0.0303 0.0305 0.0323 0.0324 9.42 1.318 0.0392 0.0374 0.0383 0.0406 0.0405 Tabulated from data in file PG01780.DAT & reduced using program Q05.01D File BW3T.DRG created on 09-12-1997 at 13:39:49 using program FORMAT