XFOIL Version 6.96 Calculated polar for: AH 85-L-120/17 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -11.750 -0.5922 0.10399 0.09698 -0.0350 1.0000 0.0441 -11.500 -0.6056 0.09587 0.08888 -0.0402 1.0000 0.0427 -11.250 -0.6261 0.08832 0.08133 -0.0451 1.0000 0.0419 -11.000 -0.6523 0.08167 0.07462 -0.0485 1.0000 0.0411 -10.750 -0.6933 0.07564 0.06835 -0.0500 1.0000 0.0395 -10.500 -0.7146 0.07216 0.06468 -0.0489 1.0000 0.0390 -10.250 -0.7302 0.06897 0.06137 -0.0469 1.0000 0.0392 -10.000 -0.7464 0.06612 0.05837 -0.0438 1.0000 0.0392 -9.750 -0.7595 0.06364 0.05565 -0.0403 1.0000 0.0388 -9.500 -0.7690 0.06062 0.05242 -0.0371 1.0000 0.0390 -9.250 -0.7768 0.05784 0.04940 -0.0335 1.0000 0.0391 -9.000 -0.7823 0.05549 0.04679 -0.0297 1.0000 0.0389 -8.750 -0.7872 0.05273 0.04379 -0.0258 1.0000 0.0393 -8.500 -0.7893 0.05036 0.04113 -0.0219 1.0000 0.0394 -8.250 -0.7887 0.04808 0.03860 -0.0183 1.0000 0.0397 -8.000 -0.7850 0.04574 0.03599 -0.0149 1.0000 0.0402 -7.750 -0.7775 0.04340 0.03336 -0.0119 1.0000 0.0411 -7.500 -0.7662 0.04134 0.03103 -0.0095 1.0000 0.0419 -7.250 -0.7533 0.03951 0.02889 -0.0072 1.0000 0.0443 -7.000 -0.7372 0.03780 0.02685 -0.0052 1.0000 0.0479 -6.750 -0.7140 0.03609 0.02472 -0.0040 1.0000 0.0505 -6.500 -0.6840 0.03403 0.02268 -0.0041 1.0000 0.0537 -6.250 -0.6602 0.03268 0.02119 -0.0031 1.0000 0.0596 -6.000 -0.6409 0.03153 0.01991 -0.0016 1.0000 0.0664 -5.750 -0.6275 0.03048 0.01873 0.0009 1.0000 0.0740 -5.500 -0.6181 0.02933 0.01751 0.0039 1.0000 0.0824 -5.250 -0.6104 0.02822 0.01645 0.0070 1.0000 0.1010 -5.000 -0.6060 0.02681 0.01536 0.0105 1.0000 0.1353 -4.750 -0.6093 0.02486 0.01427 0.0149 1.0000 0.2427 -4.500 -0.6178 0.02279 0.01381 0.0212 1.0000 0.4748 -4.250 -0.5826 0.02552 0.01742 0.0272 1.0000 0.7416 -4.000 -0.5676 0.02727 0.01892 0.0329 1.0000 0.8000 -3.750 -0.5384 0.02829 0.01954 0.0346 1.0000 0.8314 -3.500 -0.4902 0.02908 0.01990 0.0323 1.0000 0.8532 -3.250 -0.4633 0.02924 0.01977 0.0328 1.0000 0.8731 -3.000 -0.4215 0.02935 0.01956 0.0301 1.0000 0.8873 -2.750 -0.3791 0.02930 0.01917 0.0269 1.0000 0.8976 -2.500 -0.3469 0.02912 0.01876 0.0253 1.0000 0.9071 -2.250 -0.3211 0.02892 0.01838 0.0248 1.0000 0.9173 -2.000 -0.2915 0.02873 0.01798 0.0235 1.0000 0.9260 -1.750 -0.2611 0.02854 0.01764 0.0219 1.0000 0.9338 -1.500 -0.2349 0.02839 0.01737 0.0211 0.9990 0.9425 -1.250 -0.1919 0.02825 0.01710 0.0168 0.9954 0.9473 -1.000 -0.1539 0.02817 0.01688 0.0136 0.9915 0.9535 -0.750 -0.1161 0.02810 0.01673 0.0104 0.9874 0.9591 -0.500 -0.0758 0.02805 0.01662 0.0066 0.9833 0.9641 -0.250 -0.0408 0.02805 0.01658 0.0039 0.9787 0.9699 0.000 0.0001 0.02800 0.01652 0.0000 0.9739 0.9740 0.250 0.0408 0.02805 0.01658 -0.0039 0.9697 0.9786 0.500 0.0756 0.02805 0.01662 -0.0065 0.9640 0.9832 0.750 0.1162 0.02810 0.01673 -0.0103 0.9591 0.9874 1.000 0.1541 0.02817 0.01688 -0.0136 0.9535 0.9915 1.250 0.1920 0.02825 0.01709 -0.0168 0.9474 0.9955 1.500 0.2352 0.02839 0.01736 -0.0211 0.9427 0.9990 1.750 0.2605 0.02854 0.01764 -0.0218 0.9340 1.0000 2.000 0.2914 0.02873 0.01801 -0.0235 0.9262 1.0000 2.250 0.3212 0.02891 0.01837 -0.0248 0.9173 1.0000 2.500 0.3469 0.02911 0.01875 -0.0253 0.9071 1.0000 2.750 0.3793 0.02929 0.01915 -0.0269 0.8974 1.0000 3.000 0.4216 0.02935 0.01950 -0.0301 0.8873 1.0000 3.250 0.4629 0.02925 0.01978 -0.0327 0.8731 1.0000 3.500 0.4900 0.02908 0.01989 -0.0323 0.8534 1.0000 3.750 0.5380 0.02829 0.01953 -0.0346 0.8315 1.0000 4.000 0.5671 0.02726 0.01892 -0.0328 0.7996 1.0000 4.250 0.5836 0.02553 0.01743 -0.0273 0.7428 1.0000 4.500 0.6179 0.02278 0.01386 -0.0213 0.4821 1.0000 4.750 0.6097 0.02482 0.01425 -0.0150 0.2462 1.0000 5.000 0.6065 0.02675 0.01533 -0.0106 0.1378 1.0000 5.250 0.6102 0.02827 0.01648 -0.0070 0.0971 1.0000 5.500 0.6181 0.02935 0.01752 -0.0039 0.0820 1.0000 5.750 0.6277 0.03050 0.01878 -0.0008 0.0732 1.0000 6.000 0.6404 0.03159 0.01992 0.0016 0.0649 1.0000 6.250 0.6596 0.03270 0.02121 0.0032 0.0573 1.0000 6.500 0.6835 0.03402 0.02266 0.0041 0.0534 1.0000 6.750 0.7144 0.03611 0.02476 0.0039 0.0504 1.0000 7.000 0.7371 0.03785 0.02693 0.0053 0.0471 1.0000 7.250 0.7535 0.03956 0.02893 0.0072 0.0442 1.0000 7.500 0.7662 0.04134 0.03102 0.0095 0.0419 1.0000 7.750 0.7776 0.04348 0.03345 0.0120 0.0409 1.0000 8.000 0.7848 0.04579 0.03601 0.0149 0.0400 1.0000 8.250 0.7885 0.04819 0.03867 0.0182 0.0394 1.0000 8.500 0.7891 0.05050 0.04126 0.0219 0.0392 1.0000 8.750 0.7866 0.05310 0.04411 0.0257 0.0389 1.0000 9.000 0.7819 0.05571 0.04698 0.0296 0.0388 1.0000 9.250 0.7764 0.05806 0.04960 0.0334 0.0389 1.0000 9.500 0.7691 0.06067 0.05245 0.0370 0.0389 1.0000 9.750 0.7590 0.06377 0.05577 0.0403 0.0388 1.0000 10.000 0.7472 0.06681 0.05897 0.0433 0.0386 1.0000 10.250 0.7325 0.06937 0.06171 0.0464 0.0387 1.0000 10.500 0.7155 0.07248 0.06495 0.0487 0.0387 1.0000 10.750 0.6949 0.07580 0.06847 0.0500 0.0391 1.0000 11.000 0.6542 0.08152 0.07445 0.0486 0.0409 1.0000 11.250 0.6270 0.08827 0.08127 0.0452 0.0416 1.0000 11.500 0.6056 0.09605 0.08906 0.0400 0.0428 1.0000 11.750 0.5922 0.10420 0.09717 0.0348 0.0438 1.0000