Airfoil: SG6043 Builder: M. Allen Comment: clean Number of Reynolds #'s: 9 Average Reynolds #: 99681 Number of angles of attack: 16 alpha / Cl / Cd / Spanwise Cd's >>> -4.32 -0.278 0.0888 0.0865 0.0873 0.0891 0.0922 -3.07 0.047 0.0428 0.0428 0.0430 0.0421 0.0433 -1.89 0.190 0.0332 0.0324 0.0323 0.0339 0.0343 -0.87 0.300 0.0338 0.0361 0.0314 0.0323 0.0354 0.10 0.379 0.0330 0.0336 0.0320 0.0318 0.0344 1.13 0.483 0.0383 0.0382 0.0368 0.0381 0.0399 2.25 0.616 0.0428 0.0435 0.0429 0.0421 0.0426 2.95 0.708 0.0427 0.0440 0.0420 0.0422 0.0425 4.20 0.961 0.0359 0.0368 0.0356 0.0343 0.0370 5.10 1.095 0.0298 0.0309 0.0281 0.0288 0.0313 6.08 1.203 0.0235 0.0249 0.0232 0.0231 0.0229 7.27 1.285 0.0218 0.0224 0.0222 0.0214 0.0211 8.39 1.366 0.0230 0.0239 0.0234 0.0223 0.0225 9.35 1.413 0.0257 0.0258 0.0258 0.0250 0.0261 10.33 1.424 0.0295 0.0295 0.0308 0.0308 0.0268 11.30 1.432 0.0364 0.0383 0.0354 0.0374 0.0346 Tabulated from data in file pg02385.dat & reduced using program C06.01 Average Reynolds #: 149877 Number of angles of attack: 17 alpha / Cl / Cd / Spanwise Cd's >>> -4.01 -0.071 0.0623 0.0656 0.0617 0.0599 0.0618 -3.18 0.141 0.0391 0.0400 0.0386 0.0384 0.0396 -2.22 0.269 0.0308 0.0313 0.0306 0.0307 0.0305 -0.69 0.466 0.0276 0.0278 0.0276 0.0273 0.0276 0.37 0.601 0.0247 0.0247 0.0247 0.0247 0.0248 1.34 0.745 0.0236 0.0241 0.0234 0.0231 0.0237 2.33 0.873 0.0216 0.0220 0.0212 0.0216 0.0217 2.95 0.946 0.0206 0.0211 0.0199 0.0209 0.0206 4.56 1.110 0.0182 0.0187 0.0179 0.0183 0.0179 5.43 1.192 0.0173 0.0178 0.0174 0.0175 0.0166 6.72 1.313 0.0177 0.0180 0.0178 0.0184 0.0167 7.12 1.348 0.0184 0.0183 0.0187 0.0190 0.0177 8.51 1.438 0.0212 0.0212 0.0219 0.0220 0.0198 9.40 1.473 0.0252 0.0243 0.0249 0.0268 0.0248 10.41 1.490 0.0339 0.0324 0.0332 0.0345 0.0353 11.58 1.521 0.0408 0.0389 0.0393 0.0443 0.0407 12.43 1.538 0.0483 0.0430 0.0452 0.0569 0.0481 Tabulated from data in file pg02500.dat & reduced using program C06.01 Average Reynolds #: 199784 Number of angles of attack: 17 alpha / Cl / Cd / Spanwise Cd's >>> -4.95 -0.122 0.0750 0.0766 0.0744 0.0728 0.0761 -3.91 0.142 0.0395 0.0416 0.0387 0.0383 0.0396 -2.93 0.303 0.0257 0.0261 0.0251 0.0257 0.0260 -1.85 0.454 0.0210 0.0213 0.0207 0.0209 0.0211 -0.97 0.570 0.0186 0.0188 0.0183 0.0185 0.0188 0.08 0.682 0.0162 0.0162 0.0162 0.0161 0.0162 1.07 0.793 0.0154 0.0155 0.0154 0.0154 0.0155 2.20 0.915 0.0148 0.0147 0.0148 0.0148 0.0148 3.36 1.038 0.0145 0.0149 0.0143 0.0145 0.0144 3.97 1.095 0.0143 0.0148 0.0143 0.0143 0.0140 5.32 1.228 0.0143 0.0146 0.0144 0.0144 0.0139 6.46 1.325 0.0153 0.0155 0.0158 0.0153 0.0145 7.55 1.403 0.0172 0.0173 0.0174 0.0178 0.0164 8.59 1.458 0.0201 0.0197 0.0197 0.0214 0.0196 9.56 1.493 0.0245 0.0241 0.0238 0.0255 0.0245 10.20 1.507 0.0285 0.0278 0.0280 0.0295 0.0289 11.44 1.542 0.0352 0.0340 0.0333 0.0374 0.0363 Tabulated from data in file pg02387.dat & reduced using program C06.01 Average Reynolds #: 199052 Number of angles of attack: 2 alpha / Cl / Cd / Spanwise Cd's >>> 12.28 1.563 0.0404 0.0391 0.0373 0.0446 0.0407 13.61 1.576 0.0507 0.0561 0.0561 0.0524 0.0384 Tabulated from data in file pg02388.dat & reduced using program C06.01 Average Reynolds #: 299102 Number of angles of attack: 20 alpha / Cl / Cd / Spanwise Cd's >>> -6.23 -0.124 0.0864 0.0907 0.0830 0.0846 0.0874 -5.20 0.052 0.0583 0.0604 0.0567 0.0570 0.0590 -4.13 0.271 0.0240 0.0254 0.0234 0.0236 0.0236 -3.05 0.401 0.0158 0.0162 0.0153 0.0158 0.0158 -2.05 0.517 0.0136 0.0136 0.0137 0.0137 0.0135 -1.02 0.631 0.0121 0.0123 0.0123 0.0122 0.0118 -0.02 0.733 0.0109 0.0108 0.0111 0.0112 0.0107 1.05 0.840 0.0106 0.0103 0.0109 0.0108 0.0105 2.17 0.958 0.0108 0.0107 0.0108 0.0109 0.0106 3.12 1.053 0.0108 0.0108 0.0108 0.0110 0.0107 4.17 1.158 0.0110 0.0112 0.0110 0.0110 0.0110 5.18 1.249 0.0119 0.0123 0.0120 0.0118 0.0115 6.35 1.349 0.0135 0.0138 0.0136 0.0137 0.0130 7.19 1.410 0.0154 0.0156 0.0154 0.0157 0.0148 8.25 1.467 0.0187 0.0184 0.0188 0.0192 0.0184 9.34 1.511 0.0230 0.0225 0.0229 0.0239 0.0228 10.31 1.540 0.0282 0.0270 0.0273 0.0304 0.0281 11.33 1.570 0.0343 0.0343 0.0316 0.0369 0.0344 12.32 1.592 0.0408 0.0411 0.0360 0.0431 0.0429 13.30 1.607 0.0519 0.0516 0.0463 0.0561 0.0536 Tabulated from data in file pg02390.dat & reduced using program C06.01 Average Reynolds #: 302510 Number of angles of attack: 1 alpha / Cl / Cd / Spanwise Cd's >>> -5.73 -0.051 0.0740 0.0776 0.0727 0.0701 0.0756 Tabulated from data in file pg02391.dat & reduced using program C06.01 Average Reynolds #: 399643 Number of angles of attack: 6 alpha / Cl / Cd / Spanwise Cd's >>> -6.25 -0.051 0.0776 0.0826 0.0749 0.0751 0.0779 -5.21 0.118 0.0498 0.0511 0.0497 0.0490 0.0493 -4.11 0.305 0.0171 0.0181 0.0168 0.0167 0.0169 -3.09 0.418 0.0124 0.0126 0.0120 0.0125 0.0125 -2.02 0.539 0.0111 0.0110 0.0111 0.0112 0.0110 -0.96 0.656 0.0102 0.0102 0.0103 0.0101 0.0101 Tabulated from data in file pg02393.dat & reduced using program C06.01 Average Reynolds #: 398416 Number of angles of attack: 13 alpha / Cl / Cd / Spanwise Cd's >>> -0.02 0.755 0.0095 0.0094 0.0098 0.0094 0.0093 1.04 0.858 0.0088 0.0087 0.0092 0.0088 0.0086 2.03 0.961 0.0090 0.0091 0.0094 0.0090 0.0087 3.06 1.066 0.0093 0.0094 0.0097 0.0090 0.0090 4.10 1.168 0.0099 0.0100 0.0103 0.0096 0.0097 5.13 1.261 0.0109 0.0111 0.0112 0.0106 0.0107 6.14 1.344 0.0126 0.0129 0.0128 0.0124 0.0124 7.21 1.417 0.0151 0.0151 0.0152 0.0151 0.0149 8.18 1.468 0.0182 0.0181 0.0181 0.0186 0.0179 9.27 1.516 0.0220 0.0215 0.0216 0.0231 0.0219 10.32 1.554 0.0271 0.0266 0.0262 0.0284 0.0271 11.33 1.587 0.0328 0.0324 0.0305 0.0344 0.0341 12.38 1.614 0.0419 0.0422 0.0367 0.0435 0.0451 Tabulated from data in file pg02394.dat & reduced using program C06.01 Average Reynolds #: 498423 Number of angles of attack: 19 alpha / Cl / Cd / Spanwise Cd's >>> -6.32 -0.036 0.0763 0.0778 0.0762 0.0751 0.0762 -5.22 0.143 0.0459 0.0471 0.0453 0.0451 0.0462 -4.17 0.316 0.0134 0.0139 0.0131 0.0132 0.0134 -3.17 0.433 0.0108 0.0112 0.0105 0.0108 0.0108 -2.12 0.550 0.0098 0.0100 0.0098 0.0098 0.0099 -1.08 0.667 0.0092 0.0093 0.0093 0.0092 0.0092 -0.06 0.782 0.0085 0.0084 0.0087 0.0084 0.0084 1.00 0.883 0.0080 0.0078 0.0084 0.0078 0.0079 2.11 0.997 0.0084 0.0081 0.0089 0.0082 0.0083 3.15 1.101 0.0088 0.0088 0.0093 0.0086 0.0087 4.20 1.201 0.0096 0.0096 0.0099 0.0094 0.0095 5.20 1.288 0.0109 0.0111 0.0112 0.0106 0.0106 6.17 1.360 0.0127 0.0130 0.0130 0.0125 0.0124 7.29 1.433 0.0156 0.0158 0.0157 0.0157 0.0152 8.18 1.482 0.0183 0.0185 0.0182 0.0185 0.0179 9.22 1.530 0.0226 0.0224 0.0216 0.0235 0.0229 10.21 1.566 0.0269 0.0267 0.0254 0.0286 0.0270 11.22 1.599 0.0328 0.0329 0.0290 0.0337 0.0355 12.28 1.627 0.0409 0.0409 0.0351 0.0412 0.0463 Tabulated from data in file pg02397.dat & reduced using program C06.01 File sg6043.drg created using program C06.01 on Mon Feb 02 15:11:43 1998