XFOIL Version 6.96 Calculated polar for: AG47c -03f 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -8.250 -0.6441 0.11477 0.11258 0.0373 1.0000 0.0108 -8.000 -0.6493 0.10848 0.10633 0.0354 1.0000 0.0111 -7.750 -0.6454 0.10505 0.10291 0.0351 1.0000 0.0115 -7.500 -0.6403 0.10177 0.09962 0.0343 1.0000 0.0118 -7.250 -0.6360 0.09826 0.09613 0.0327 1.0000 0.0121 -7.000 -0.6319 0.09463 0.09251 0.0307 1.0000 0.0124 -6.750 -0.6278 0.09082 0.08873 0.0282 1.0000 0.0128 -6.500 -0.6217 0.08672 0.08465 0.0244 1.0000 0.0132 -6.250 -0.6109 0.08207 0.07999 0.0190 1.0000 0.0140 -6.000 -0.5965 0.07685 0.07476 0.0124 1.0000 0.0149 -5.750 -0.5751 0.07086 0.06873 0.0040 1.0000 0.0159 -5.500 -0.5493 0.06549 0.06328 -0.0028 1.0000 0.0165 -5.250 -0.5265 0.06012 0.05780 -0.0078 1.0000 0.0167 -5.000 -0.5038 0.05470 0.05224 -0.0118 1.0000 0.0168 -4.750 -0.4810 0.04941 0.04677 -0.0149 1.0000 0.0168 -4.500 -0.4654 0.03951 0.03652 -0.0196 1.0000 0.0177 -4.250 -0.4441 0.03621 0.03310 -0.0208 1.0000 0.0184 -4.000 -0.4205 0.03332 0.03005 -0.0217 1.0000 0.0192 -3.750 -0.3953 0.03030 0.02682 -0.0224 1.0000 0.0203 -3.500 -0.3687 0.02717 0.02339 -0.0228 1.0000 0.0219 -3.250 -0.3384 0.02657 0.02250 -0.0221 1.0000 0.0254 -3.000 -0.3110 0.01769 0.01275 -0.0221 1.0000 0.0151 -2.750 -0.2826 0.01381 0.00827 -0.0215 1.0000 0.0131 -2.500 -0.2550 0.01233 0.00659 -0.0210 1.0000 0.0138 -2.250 -0.2275 0.01129 0.00542 -0.0206 1.0000 0.0149 -2.000 -0.1999 0.01093 0.00501 -0.0204 1.0000 0.0166 -1.750 -0.1729 0.00951 0.00346 -0.0200 1.0000 0.0183 -1.500 -0.1453 0.00879 0.00270 -0.0198 1.0000 0.0214 -1.250 -0.1174 0.00821 0.00207 -0.0195 1.0000 0.0291 -1.000 -0.0898 0.00772 0.00169 -0.0194 1.0000 0.0561 -0.750 -0.0624 0.00717 0.00148 -0.0194 1.0000 0.1381 -0.500 -0.0354 0.00653 0.00134 -0.0196 1.0000 0.2807 -0.250 -0.0065 0.00551 0.00127 -0.0204 0.9910 0.5559 0.000 0.0231 0.00441 0.00127 -0.0201 0.9178 0.8945 0.250 0.0565 0.00455 0.00112 -0.0204 0.8208 1.0000 0.500 0.0818 0.00479 0.00105 -0.0196 0.7764 1.0000 0.750 0.1084 0.00496 0.00102 -0.0191 0.7508 1.0000 1.000 0.1354 0.00513 0.00101 -0.0188 0.7317 1.0000 1.250 0.1626 0.00527 0.00103 -0.0185 0.7153 1.0000 1.500 0.1900 0.00541 0.00105 -0.0182 0.7002 1.0000 1.750 0.2176 0.00549 0.00107 -0.0180 0.6837 1.0000 2.000 0.2453 0.00553 0.00107 -0.0178 0.6653 1.0000 2.250 0.2729 0.00558 0.00106 -0.0176 0.6435 1.0000 2.500 0.3004 0.00566 0.00106 -0.0174 0.6169 1.0000 2.750 0.3278 0.00578 0.00107 -0.0172 0.5853 1.0000 3.000 0.3550 0.00596 0.00110 -0.0169 0.5454 1.0000 3.250 0.3821 0.00617 0.00115 -0.0167 0.5029 1.0000 3.500 0.4091 0.00645 0.00125 -0.0166 0.4492 1.0000 3.750 0.4361 0.00678 0.00137 -0.0165 0.3935 1.0000 4.000 0.4630 0.00715 0.00151 -0.0164 0.3345 1.0000 4.250 0.4898 0.00759 0.00170 -0.0163 0.2699 1.0000 4.500 0.5166 0.00803 0.00191 -0.0163 0.2156 1.0000 4.750 0.5435 0.00847 0.00218 -0.0163 0.1697 1.0000 5.000 0.5704 0.00889 0.00245 -0.0162 0.1334 1.0000 5.250 0.5974 0.00928 0.00275 -0.0162 0.1095 1.0000 5.500 0.6243 0.00968 0.00307 -0.0161 0.0912 1.0000 5.750 0.6511 0.01011 0.00347 -0.0160 0.0764 1.0000 6.000 0.6781 0.01045 0.00381 -0.0159 0.0664 1.0000 6.250 0.7050 0.01082 0.00421 -0.0157 0.0573 1.0000 6.500 0.7316 0.01133 0.00472 -0.0156 0.0490 1.0000 6.750 0.7581 0.01179 0.00518 -0.0154 0.0419 1.0000 7.000 0.7845 0.01232 0.00581 -0.0152 0.0362 1.0000 7.250 0.8107 0.01288 0.00639 -0.0151 0.0308 1.0000 7.500 0.8359 0.01382 0.00745 -0.0147 0.0273 1.0000 7.750 0.8619 0.01446 0.00818 -0.0144 0.0246 1.0000 8.000 0.8875 0.01514 0.00892 -0.0142 0.0220 1.0000 8.250 0.9095 0.01718 0.01119 -0.0136 0.0193 1.0000 8.500 0.9347 0.01800 0.01216 -0.0133 0.0184 1.0000 8.750 0.9589 0.01921 0.01355 -0.0128 0.0173 1.0000 9.000 0.9827 0.02048 0.01501 -0.0124 0.0161 1.0000 9.250 1.0070 0.02122 0.01584 -0.0122 0.0148 1.0000 9.500 1.0280 0.02310 0.01791 -0.0118 0.0134 1.0000 9.750 1.0392 0.02848 0.02395 -0.0110 0.0126 1.0000 10.000 1.0594 0.03024 0.02599 -0.0106 0.0122 1.0000 10.250 1.0745 0.03330 0.02948 -0.0102 0.0117 1.0000 10.500 1.0854 0.03697 0.03356 -0.0100 0.0111 1.0000 10.750 1.0945 0.04044 0.03737 -0.0101 0.0104 1.0000 11.000 1.1090 0.04207 0.03914 -0.0102 0.0097 1.0000 11.250 1.1198 0.04414 0.04137 -0.0106 0.0092 1.0000 11.500 1.1142 0.04893 0.04645 -0.0122 0.0090 1.0000 11.750 0.9611 0.09330 0.09135 -0.0479 0.0127 1.0000 12.000 0.9513 0.10124 0.09929 -0.0518 0.0129 1.0000