XFOIL Version 6.94 Calculated polar for: SD5060 (9.5%) 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.080 Re = 0.300 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- 0.000 0.2550 0.00718 0.00265 -0.0518 0.7735 0.9730 0.500 0.3184 0.00721 0.00246 -0.0530 0.7483 1.0000 1.000 0.3713 0.00732 0.00240 -0.0521 0.7202 1.0000 1.500 0.4249 0.00746 0.00238 -0.0512 0.6915 1.0000 2.000 0.4788 0.00764 0.00241 -0.0504 0.6596 1.0000 2.500 0.5328 0.00785 0.00248 -0.0496 0.6233 1.0000 3.000 0.5865 0.00813 0.00261 -0.0489 0.5828 1.0000 3.500 0.6400 0.00847 0.00280 -0.0482 0.5360 1.0000 4.000 0.6924 0.00896 0.00308 -0.0473 0.4794 1.0000 4.500 0.7439 0.00958 0.00346 -0.0465 0.4138 1.0000 5.000 0.7941 0.01040 0.00398 -0.0456 0.3391 1.0000 5.500 0.8434 0.01137 0.00467 -0.0447 0.2723 1.0000 6.000 0.8924 0.01238 0.00546 -0.0438 0.2212 1.0000 6.500 0.9410 0.01342 0.00636 -0.0429 0.1847 1.0000 7.000 0.9897 0.01439 0.00731 -0.0418 0.1580 1.0000 7.500 1.0368 0.01549 0.00834 -0.0407 0.1360 1.0000 8.000 1.0830 0.01664 0.00953 -0.0394 0.1179 1.0000 8.500 1.1287 0.01774 0.01072 -0.0381 0.1012 1.0000 9.000 1.1729 0.01891 0.01200 -0.0366 0.0846 1.0000 9.500 1.2157 0.02007 0.01323 -0.0350 0.0678 1.0000 10.500 1.2891 0.02316 0.01648 -0.0306 0.0414 1.0000 11.000 1.3155 0.02521 0.01865 -0.0273 0.0306 1.0000 12.000 1.3189 0.03227 0.02608 -0.0172 0.0186 1.0000 12.500 1.3216 0.03641 0.03049 -0.0145 0.0163 1.0000 13.000 1.3155 0.04195 0.03623 -0.0131 0.0149 1.0000 14.000 1.2890 0.05711 0.05203 -0.0146 0.0134 1.0000 14.500 1.2758 0.06592 0.06117 -0.0179 0.0126 1.0000 15.000 1.2574 0.07644 0.07202 -0.0228 0.0122 1.0000 15.500 1.2342 0.08881 0.08472 -0.0293 0.0120 1.0000 16.000 1.2062 0.10332 0.09958 -0.0376 0.0118 1.0000 16.500 1.1731 0.11998 0.11656 -0.0474 0.0120 1.0000 17.000 1.1325 0.13986 0.13677 -0.0595 0.0122 1.0000 17.500 1.0620 0.17040 0.16766 -0.0780 0.0136 1.0000 18.000 0.9711 0.22160 0.21878 -0.1023 0.0188 1.0000 20.000 0.7894 0.24587 0.24366 -0.1116 0.0240 1.0000 20.500 0.7990 0.25394 0.25174 -0.1151 0.0219 1.0000 21.000 0.8100 0.26132 0.25915 -0.1181 0.0207 1.0000 21.500 0.8252 0.27131 0.26918 -0.1196 0.0196 1.0000 22.000 0.8318 0.28025 0.27814 -0.1236 0.0195 1.0000 22.500 0.8345 0.28920 0.28709 -0.1290 0.0190 1.0000 23.000 0.8415 0.29857 0.29648 -0.1333 0.0167 1.0000 23.500 0.8501 0.30693 0.30487 -0.1366 0.0154 1.0000 24.000 0.8613 0.31443 0.31239 -0.1391 0.0143 1.0000 24.500 0.8717 0.32540 0.32338 -0.1417 0.0139 1.0000 25.000 0.8751 0.33474 0.33273 -0.1463 0.0138 1.0000 25.500 0.8810 0.34470 0.34272 -0.1507 0.0129 1.0000 26.000 0.8883 0.35421 0.35227 -0.1541 0.0119 1.0000 26.500 0.8954 0.36342 0.36150 -0.1575 0.0111 1.0000 27.000 0.9026 0.37220 0.37031 -0.1605 0.0103 1.0000 27.500 0.9103 0.38124 0.37937 -0.1633 0.0100 1.0000 28.500 0.9207 0.40191 0.40008 -0.1702 0.0098 1.0000 29.000 0.9252 0.41221 0.41041 -0.1740 0.0095 1.0000 29.500 0.9304 0.42250 0.42073 -0.1773 0.0087 1.0000 30.000 0.9357 0.43261 0.43087 -0.1807 0.0078 1.0000 30.500 0.9402 0.44212 0.44041 -0.1839 0.0075 1.0000 31.000 0.9442 0.45157 0.44989 -0.1870 0.0071 1.0000 31.500 0.9482 0.46068 0.45903 -0.1897 0.0068 1.0000 32.500 0.9545 0.48206 0.48046 -0.1962 0.0066 1.0000 33.000 0.9572 0.49303 0.49146 -0.1995 0.0064 1.0000 33.500 0.9600 0.50326 0.50172 -0.2027 0.0062 1.0000 34.000 0.9620 0.51311 0.51159 -0.2056 0.0058 1.0000