XFOIL Version 6.94 Calculated polar for: AH 79-K-135/20 B 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.080 Re = 0.450 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- 0.000 0.2851 0.01144 0.00699 -0.0549 0.7298 0.8936 0.500 0.3333 0.01133 0.00683 -0.0524 0.7256 0.9098 1.000 0.3844 0.01134 0.00679 -0.0514 0.7203 0.9198 1.500 0.4343 0.01108 0.00657 -0.0501 0.7131 0.9313 2.000 0.4876 0.01071 0.00620 -0.0496 0.7056 0.9386 2.500 0.5444 0.01028 0.00574 -0.0498 0.6994 0.9454 3.000 0.6024 0.00988 0.00530 -0.0502 0.6926 0.9513 3.500 0.6570 0.00951 0.00505 -0.0502 0.6803 0.9577 4.000 0.7151 0.00899 0.00451 -0.0507 0.6663 0.9636 4.500 0.7752 0.00876 0.00432 -0.0518 0.6465 0.9696 5.000 0.8335 0.00861 0.00419 -0.0527 0.6220 0.9748 5.500 0.8853 0.00899 0.00409 -0.0524 0.5310 0.9813 6.000 0.9459 0.00958 0.00457 -0.0545 0.4797 0.9863 6.500 0.9222 0.01406 0.00706 -0.0443 0.1508 1.0000 7.000 0.9447 0.01505 0.00795 -0.0400 0.1191 1.0000 7.500 0.9559 0.01790 0.01028 -0.0363 0.0247 1.0000 8.000 0.9847 0.02001 0.01257 -0.0343 0.0137 1.0000 8.500 1.0144 0.02193 0.01466 -0.0325 0.0133 1.0000 9.000 1.0429 0.02390 0.01676 -0.0306 0.0132 1.0000 9.500 1.0569 0.02690 0.02000 -0.0274 0.0136 1.0000 10.000 1.0744 0.02971 0.02302 -0.0245 0.0137 1.0000 10.500 1.0917 0.03259 0.02605 -0.0220 0.0136 1.0000 11.000 1.1018 0.03630 0.02999 -0.0179 0.0144 1.0000 11.500 1.1240 0.03880 0.03256 -0.0169 0.0123 1.0000 12.000 1.1495 0.04205 0.03611 -0.0136 0.0141 1.0000 12.500 1.1618 0.04538 0.03953 -0.0124 0.0118 1.0000 13.000 1.1789 0.04911 0.04353 -0.0103 0.0113 1.0000 13.500 1.1992 0.05377 0.04862 -0.0076 0.0123 1.0000 14.000 1.1998 0.05966 0.05485 -0.0059 0.0119 1.0000 14.500 1.1916 0.06597 0.06133 -0.0056 0.0106 1.0000 15.000 1.1503 0.07813 0.07404 -0.0055 0.0099 1.0000 15.500 1.0809 0.09541 0.09192 -0.0099 0.0096 1.0000 16.000 1.1170 0.09615 0.09267 -0.0112 0.0104 1.0000 16.500 1.0594 0.11403 0.11100 -0.0193 0.0100 1.0000 17.000 1.0385 0.12705 0.12433 -0.0272 0.0105 1.0000 17.500 1.0136 0.14180 0.13932 -0.0368 0.0106 1.0000