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 = 0.100 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -7.000 -0.5070 0.08799 0.08352 0.0159 1.0000 0.0425 -6.750 -0.5071 0.08380 0.07936 0.0144 1.0000 0.0426 -6.500 -0.5077 0.07953 0.07514 0.0125 1.0000 0.0424 -6.000 -0.5868 0.08185 0.07725 0.0109 1.0000 0.0411 -5.500 -0.5522 0.06809 0.06329 -0.0030 1.0000 0.0243 -5.250 -0.5367 0.06313 0.05825 -0.0064 1.0000 0.0231 -5.000 -0.5176 0.05769 0.05268 -0.0105 1.0000 0.0220 -4.750 -0.4959 0.05200 0.04678 -0.0144 1.0000 0.0210 -4.500 -0.4722 0.04649 0.04097 -0.0175 1.0000 0.0206 -4.250 -0.4475 0.04170 0.03585 -0.0198 1.0000 0.0215 -4.000 -0.4214 0.03716 0.03086 -0.0214 1.0000 0.0227 -3.750 -0.3948 0.03296 0.02616 -0.0223 1.0000 0.0233 -3.500 -0.3678 0.02915 0.02181 -0.0228 1.0000 0.0231 -3.250 -0.3402 0.02590 0.01795 -0.0228 1.0000 0.0233 -3.000 -0.3122 0.02321 0.01474 -0.0226 1.0000 0.0238 -2.750 -0.2842 0.02103 0.01212 -0.0222 1.0000 0.0246 -2.500 -0.2567 0.01921 0.00999 -0.0218 1.0000 0.0263 -2.250 -0.2303 0.01788 0.00863 -0.0216 1.0000 0.0311 -2.000 -0.2032 0.01658 0.00718 -0.0211 1.0000 0.0349 -1.750 -0.1766 0.01540 0.00593 -0.0207 1.0000 0.0413 -1.500 -0.1498 0.01449 0.00499 -0.0203 1.0000 0.0532 -1.250 -0.1230 0.01364 0.00423 -0.0201 1.0000 0.0798 -1.000 -0.0966 0.01267 0.00364 -0.0199 1.0000 0.1579 -0.750 -0.0719 0.01133 0.00331 -0.0199 1.0000 0.4013 -0.500 -0.0556 0.00968 0.00319 -0.0161 1.0000 0.8417 -0.250 -0.0149 0.00945 0.00283 -0.0183 1.0000 1.0000 0.000 0.0118 0.00944 0.00264 -0.0181 1.0000 1.0000 0.250 0.0384 0.00944 0.00251 -0.0179 1.0000 1.0000 0.500 0.0650 0.00945 0.00240 -0.0177 1.0000 1.0000 0.750 0.0914 0.00948 0.00236 -0.0176 1.0000 1.0000 1.000 0.1231 0.00954 0.00236 -0.0186 0.9838 1.0000 1.250 0.1654 0.00965 0.00238 -0.0216 0.9276 1.0000 1.500 0.2036 0.00978 0.00237 -0.0233 0.8691 1.0000 1.750 0.2335 0.00997 0.00238 -0.0231 0.8203 1.0000 2.000 0.2596 0.01020 0.00243 -0.0222 0.7822 1.0000 2.250 0.2850 0.01046 0.00252 -0.0212 0.7503 1.0000 2.500 0.3106 0.01074 0.00266 -0.0202 0.7218 1.0000 2.750 0.3361 0.01103 0.00283 -0.0194 0.6951 1.0000 3.000 0.3623 0.01121 0.00300 -0.0188 0.6626 1.0000 3.250 0.3881 0.01139 0.00313 -0.0181 0.6275 1.0000 3.500 0.4139 0.01157 0.00327 -0.0174 0.5864 1.0000 3.750 0.4394 0.01180 0.00338 -0.0166 0.5380 1.0000 4.000 0.4648 0.01213 0.00351 -0.0159 0.4809 1.0000 4.250 0.4900 0.01256 0.00370 -0.0153 0.4168 1.0000 4.500 0.5152 0.01310 0.00398 -0.0148 0.3475 1.0000 4.750 0.5405 0.01375 0.00440 -0.0145 0.2795 1.0000 5.000 0.5658 0.01444 0.00486 -0.0143 0.2218 1.0000 5.250 0.5913 0.01517 0.00540 -0.0141 0.1770 1.0000 5.500 0.6169 0.01589 0.00603 -0.0139 0.1472 1.0000 5.750 0.6424 0.01663 0.00676 -0.0137 0.1233 1.0000 6.000 0.6678 0.01741 0.00754 -0.0134 0.1067 1.0000 6.250 0.6930 0.01823 0.00839 -0.0131 0.0926 1.0000 6.500 0.7182 0.01907 0.00928 -0.0128 0.0798 1.0000 6.750 0.7429 0.02013 0.01043 -0.0124 0.0712 1.0000 7.000 0.7674 0.02115 0.01154 -0.0121 0.0620 1.0000 7.250 0.7921 0.02222 0.01279 -0.0117 0.0545 1.0000 7.500 0.8157 0.02377 0.01443 -0.0112 0.0496 1.0000 7.750 0.8403 0.02496 0.01588 -0.0108 0.0432 1.0000 8.000 0.8627 0.02673 0.01770 -0.0105 0.0392 1.0000 8.250 0.8861 0.02895 0.02039 -0.0099 0.0366 1.0000 8.500 0.9083 0.03126 0.02318 -0.0094 0.0334 1.0000 8.750 0.9297 0.03270 0.02479 -0.0092 0.0301 1.0000 9.000 0.9474 0.03600 0.02844 -0.0090 0.0283 1.0000 9.250 0.9626 0.04012 0.03327 -0.0087 0.0272 1.0000 9.500 0.9720 0.04530 0.03915 -0.0088 0.0264 1.0000 9.750 0.9744 0.05136 0.04584 -0.0097 0.0260 1.0000 10.000 0.9691 0.05802 0.05301 -0.0118 0.0257 1.0000 10.250 0.9562 0.06520 0.06054 -0.0156 0.0257 1.0000 10.500 0.9372 0.07304 0.06855 -0.0225 0.0262 1.0000 10.750 0.9177 0.08419 0.07973 -0.0332 0.0268 1.0000