XFOIL Version 6.96 Calculated polar for: FX 63-147 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -13.000 -0.3848 0.13860 0.13691 -0.0309 1.0001 0.0068 -12.750 -0.3817 0.13546 0.13378 -0.0316 1.0001 0.0068 -12.500 -0.3795 0.13202 0.13035 -0.0324 1.0001 0.0069 -12.250 -0.3773 0.12869 0.12703 -0.0331 1.0001 0.0070 -12.000 -0.3761 0.12512 0.12348 -0.0339 1.0001 0.0071 -11.750 -0.3754 0.12153 0.11990 -0.0347 1.0001 0.0072 -11.500 -0.3756 0.11779 0.11617 -0.0355 1.0001 0.0073 -11.250 -0.3765 0.11397 0.11238 -0.0363 1.0001 0.0074 -11.000 -0.3784 0.11005 0.10847 -0.0372 1.0001 0.0075 -10.750 -0.3813 0.10599 0.10443 -0.0380 1.0001 0.0076 -9.500 -0.3809 0.06605 0.06448 -0.0755 0.9931 0.0079 -9.250 -0.3951 0.05776 0.05605 -0.0841 0.9882 0.0078 -9.000 -0.4030 0.05081 0.04890 -0.0905 0.9846 0.0080 -7.000 -0.2425 0.00948 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0.8099 3.000 0.8656 0.00837 0.00320 -0.1165 0.4297 0.8118 3.250 0.8904 0.00861 0.00334 -0.1160 0.4109 0.8139 3.500 0.9161 0.00884 0.00350 -0.1158 0.3897 0.8160 3.750 0.9420 0.00910 0.00366 -0.1157 0.3677 0.8181 4.000 0.9685 0.00937 0.00382 -0.1157 0.3484 0.8202 4.250 0.9955 0.00964 0.00400 -0.1158 0.3281 0.8223 4.500 1.0203 0.00998 0.00422 -0.1156 0.3025 0.8240 4.750 1.0407 0.01049 0.00454 -0.1144 0.2631 0.8257 5.000 1.0597 0.01110 0.00493 -0.1130 0.2224 0.8275 5.250 1.0759 0.01193 0.00548 -0.1112 0.1678 0.8296 5.500 1.0920 0.01279 0.00607 -0.1094 0.1164 0.8317 5.750 1.1109 0.01348 0.00658 -0.1081 0.0801 0.8337 6.000 1.1320 0.01401 0.00699 -0.1072 0.0588 0.8356 6.250 1.1563 0.01435 0.00731 -0.1069 0.0495 0.8373 6.500 1.1761 0.01490 0.00777 -0.1058 0.0328 0.8390 6.750 1.1954 0.01521 0.00809 -0.1044 0.0274 0.8405 7.000 1.2118 0.01568 0.00854 -0.1026 0.0166 0.8421 7.250 1.2310 0.01608 0.00894 -0.1013 0.0155 0.8436 7.500 1.2510 0.01648 0.00936 -0.1001 0.0144 0.8454 7.750 1.2712 0.01688 0.00978 -0.0991 0.0137 0.8473 8.000 1.2913 0.01729 0.01023 -0.0980 0.0131 0.8493 8.250 1.3112 0.01774 0.01071 -0.0970 0.0127 0.8510 8.500 1.3310 0.01821 0.01123 -0.0961 0.0125 0.8526 8.750 1.3499 0.01871 0.01177 -0.0950 0.0121 0.8540 9.000 1.3658 0.01924 0.01237 -0.0934 0.0117 0.8555 9.250 1.3801 0.01986 0.01306 -0.0915 0.0110 0.8570 9.500 1.3924 0.02062 0.01389 -0.0895 0.0102 0.8586 9.750 1.4033 0.02149 0.01483 -0.0873 0.0095 0.8602 10.000 1.4222 0.02190 0.01527 -0.0864 0.0092 0.8617 10.250 1.4391 0.02246 0.01586 -0.0853 0.0087 0.8633 10.500 1.4553 0.02310 0.01653 -0.0842 0.0080 0.8649 10.750 1.4703 0.02386 0.01733 -0.0831 0.0074 0.8664 11.000 1.4833 0.02477 0.01827 -0.0818 0.0069 0.8678 11.250 1.4974 0.02562 0.01917 -0.0806 0.0065 0.8693 11.500 1.5102 0.02650 0.02012 -0.0794 0.0054 0.8707 11.750 1.5177 0.02781 0.02142 -0.0777 0.0032 0.8722 12.000 1.5240 0.02932 0.02300 -0.0761 0.0029 0.8736 12.250 1.5297 0.03100 0.02475 -0.0747 0.0027 0.8750 12.500 1.5353 0.03280 0.02664 -0.0736 0.0025 0.8765 12.750 1.5405 0.03474 0.02866 -0.0726 0.0024 0.8779 13.000 1.5449 0.03683 0.03084 -0.0718 0.0023 0.8794 13.250 1.5479 0.03917 0.03328 -0.0711 0.0022 0.8809 13.500 1.5500 0.04171 0.03591 -0.0706 0.0021 0.8821 13.750 1.5512 0.04437 0.03868 -0.0702 0.0021 0.8832 14.000 1.5515 0.04717 0.04158 -0.0698 0.0021 0.8844 14.250 1.5499 0.05019 0.04471 -0.0695 0.0020 0.8855 14.500 1.5474 0.05336 0.04800 -0.0693 0.0020 0.8867 14.750 1.5438 0.05676 0.05151 -0.0692 0.0020 0.8879 15.000 1.5399 0.06024 0.05510 -0.0692 0.0020 0.8891 15.250 1.5348 0.06401 0.05899 -0.0694 0.0019 0.8901 15.500 1.5295 0.06784 0.06293 -0.0697 0.0019 0.8911 15.750 1.5233 0.07189 0.06708 -0.0702 0.0019 0.8921 16.000 1.5166 0.07607 0.07137 -0.0708 0.0019 0.8930 16.250 1.5089 0.08051 0.07593 -0.0716 0.0019 0.8938 16.500 1.5013 0.08496 0.08048 -0.0724 0.0019 0.8946 16.750 1.4926 0.08961 0.08524 -0.0734 0.0018 0.8954 17.000 1.4842 0.09433 0.09007 -0.0746 0.0018 0.8961 17.250 1.4755 0.09917 0.09502 -0.0759 0.0018 0.8967 17.500 1.4666 0.10406 0.10001 -0.0773 0.0018 0.8975 17.750 1.4578 0.10896 0.10503 -0.0788 0.0018 0.8985 18.000 1.4482 0.11403 0.11021 -0.0804 0.0018 0.8993 18.250 1.4385 0.11922 0.11550 -0.0822 0.0018 0.9000 18.500 1.4300 0.12416 0.12055 -0.0841 0.0018 0.9008 18.750 1.4204 0.12951 0.12601 -0.0863 0.0018 0.9015 19.000 1.4109 0.13474 0.13135 -0.0885 0.0018 0.9022