Airfoil: Goe 417a Builder: M. Fox Comment: clean Number of Reynolds #'s: 5 Average Reynolds #: 59300 Number of angles of attack: 10 alpha / Cl / Cd / Spanwise Cd's >>> -2.25 -0.230 0.0773 0.0807 0.0843 0.0815 0.0628 -0.67 -0.066 0.0607 0.0849 0.0648 0.0526 0.0405 0.87 0.178 0.0457 0.0635 0.0477 0.0384 0.0334 2.49 0.479 0.0360 0.0431 0.0367 0.0344 0.0297 3.95 0.710 0.0364 0.0387 0.0363 0.0345 0.0363 5.62 0.984 0.0285 0.0297 0.0283 0.0289 0.0272 7.10 1.131 0.0213 0.0224 0.0206 0.0195 0.0225 8.65 1.238 0.0226 0.0234 0.0205 0.0285 0.0182 10.17 1.337 0.0283 0.0268 0.0248 0.0284 0.0332 11.76 1.398 0.0412 0.0380 0.0384 0.0411 0.0472 Tabulated from data in file PG01725.DAT & reduced using program Q05.01D Average Reynolds #: 99500 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -3.77 -0.332 0.0720 0.0742 0.0690 0.0692 0.0757 -2.20 -0.220 0.0608 0.0658 0.0614 0.0589 0.0571 -0.63 0.066 0.0450 0.0468 0.0442 0.0463 0.0427 0.87 0.341 0.0362 0.0357 0.0351 0.0351 0.0390 2.43 0.598 0.0296 0.0315 0.0272 0.0287 0.0309 4.05 0.819 0.0241 0.0231 0.0247 0.0234 0.0250 5.54 0.943 0.0191 0.0200 0.0175 0.0181 0.0209 7.06 1.076 0.0166 0.0174 0.0166 0.0146 0.0179 8.62 1.211 0.0202 0.0204 0.0175 0.0204 0.0224 10.13 1.304 0.0311 0.0283 0.0325 0.0323 0.0312 11.65 1.371 0.0441 0.0399 0.0408 0.0473 0.0484 Tabulated from data in file PG01126.DAT & reduced using program Q05.01D Average Reynolds #: 198500 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -3.73 -0.289 0.0672 0.0719 0.0623 0.0628 0.0717 -2.24 -0.027 0.0454 0.0473 0.0424 0.0460 0.0461 -0.69 0.283 0.0314 0.0319 0.0302 0.0321 0.0316 0.94 0.568 0.0209 0.0212 0.0204 0.0213 0.0208 2.57 0.759 0.0162 0.0154 0.0166 0.0158 0.0168 4.09 0.923 0.0137 0.0135 0.0139 0.0128 0.0144 5.64 1.067 0.0140 0.0137 0.0140 0.0140 0.0143 7.14 1.185 0.0163 0.0146 0.0167 0.0164 0.0174 8.66 1.272 0.0237 0.0208 0.0244 0.0248 0.0247 10.21 1.345 0.0320 0.0297 0.0320 0.0345 0.0318 11.64 1.387 0.0448 0.0395 0.0460 0.0483 0.0455 Tabulated from data in file CL01128.DAT & reduced using program Q05.01D Average Reynolds #: 297500 Number of angles of attack: 11 alpha / Cl / Cd / Spanwise Cd's >>> -3.73 -0.127 0.0556 0.0591 0.0527 0.0521 0.0582 -2.15 0.101 0.0394 0.0417 0.0376 0.0383 0.0401 -0.39 0.409 0.0252 0.0255 0.0238 0.0249 0.0264 0.94 0.590 0.0185 0.0186 0.0192 0.0206 0.0153 2.50 0.778 0.0143 0.0141 0.0144 0.0139 0.0148 4.02 0.939 0.0123 0.0125 0.0120 0.0116 0.0130 5.54 1.075 0.0129 0.0124 0.0130 0.0127 0.0132 7.15 1.199 0.0159 0.0141 0.0159 0.0171 0.0166 8.71 1.291 0.0225 0.0196 0.0229 0.0244 0.0230 10.30 1.370 0.0303 0.0271 0.0304 0.0323 0.0314 11.69 1.408 0.0436 0.0348 0.0435 0.0508 0.0450 Tabulated from data in file CL01130.DAT & reduced using program Q05.01D Average Reynolds #: 398800 Number of angles of attack: 4 alpha / Cl / Cd / Spanwise Cd's >>> -2.40 0.172 0.0364 0.0390 0.0361 0.0340 0.0367 -0.34 0.498 0.0217 0.0221 0.0209 0.0216 0.0220 1.01 0.672 0.0165 0.0174 0.0161 0.0158 0.0167 2.49 0.842 0.0133 0.0139 0.0130 0.0132 0.0132 Tabulated from data in file CL01132.DAT & reduced using program Q05.01D File GOE417A.DRG created on 09-12-1997 at 13:39:49 using program FORMAT