XFOIL Version 6.96 Calculated polar for: WORTMANN FX 057-816 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -14.000 -0.7199 0.04967 0.04516 -0.0860 0.5845 0.0095 -13.750 -0.7601 0.04245 0.03766 -0.0892 0.5843 0.0094 -13.500 -0.7783 0.03889 0.03394 -0.0887 0.5840 0.0095 -13.250 -0.7888 0.03627 0.03118 -0.0873 0.5836 0.0096 -13.000 -0.7939 0.03422 0.02900 -0.0854 0.5831 0.0097 -12.750 -0.7961 0.03252 0.02717 -0.0831 0.5826 0.0098 -12.500 -0.7968 0.03117 0.02570 -0.0804 0.5820 0.0100 -12.250 -0.7903 0.02979 0.02416 -0.0786 0.5815 0.0101 -12.000 -0.7792 0.02856 0.02280 -0.0772 0.5808 0.0103 -11.750 -0.7665 0.02737 0.02147 -0.0758 0.5802 0.0105 -11.500 -0.7514 0.02629 0.02024 -0.0747 0.5794 0.0108 -11.250 -0.7346 0.02528 0.01908 -0.0737 0.5786 0.0111 -11.000 -0.7164 0.02435 0.01801 -0.0728 0.5779 0.0114 -10.750 -0.6968 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0.00635 -0.0746 0.5446 0.8466 3.750 0.8626 0.01206 0.00640 -0.0748 0.5438 0.8497 4.000 0.8913 0.01209 0.00643 -0.0751 0.5428 0.8517 4.250 0.9181 0.01221 0.00664 -0.0753 0.5413 0.8541 4.500 0.9449 0.01236 0.00687 -0.0753 0.5399 0.8585 4.750 0.9727 0.01244 0.00700 -0.0756 0.5380 0.8622 5.000 1.0014 0.01243 0.00702 -0.0761 0.5360 0.8635 5.250 1.0302 0.01237 0.00700 -0.0765 0.5343 0.8642 5.500 1.0591 0.01233 0.00698 -0.0769 0.5328 0.8650 5.750 1.0880 0.01227 0.00695 -0.0774 0.5315 0.8659 6.000 1.1168 0.01225 0.00696 -0.0778 0.5303 0.8668 6.250 1.1452 0.01223 0.00698 -0.0782 0.5286 0.8678 6.500 1.1715 0.01236 0.00723 -0.0784 0.5256 0.8687 6.750 1.1989 0.01240 0.00736 -0.0787 0.5227 0.8697 7.000 1.2272 0.01233 0.00735 -0.0791 0.5197 0.8706 7.250 1.2559 0.01224 0.00730 -0.0795 0.5172 0.8716 7.500 1.2837 0.01224 0.00737 -0.0798 0.5144 0.8726 7.750 1.3098 0.01234 0.00760 -0.0800 0.5076 0.8738 8.000 1.3376 0.01217 0.00747 -0.0803 0.4956 0.8749 8.250 1.3646 0.01204 0.00734 -0.0804 0.4770 0.8760 8.500 1.3816 0.01238 0.00741 -0.0791 0.4276 0.8776 8.750 1.3493 0.01528 0.00983 -0.0715 0.3390 0.8816 9.000 1.3159 0.01778 0.01233 -0.0643 0.3162 0.8867 9.250 1.2772 0.02278 0.01737 -0.0607 0.3016 0.8926 9.500 1.2494 0.02632 0.02090 -0.0569 0.2881 0.8973 9.750 1.2249 0.02960 0.02414 -0.0533 0.2722 0.9027 10.000 1.2116 0.03224 0.02675 -0.0507 0.2576 0.9078 10.250 1.2035 0.03458 0.02906 -0.0486 0.2438 0.9131 10.500 1.1992 0.03668 0.03114 -0.0468 0.2293 0.9204 10.750 1.1967 0.03893 0.03335 -0.0455 0.2111 0.9302 11.000 1.1943 0.04155 0.03585 -0.0449 0.1834 0.9470 11.500 1.1869 0.04714 0.04107 -0.0437 0.1210 1.0000 11.750 1.1883 0.04944 0.04323 -0.0430 0.1016 1.0000 12.000 1.1948 0.05134 0.04510 -0.0426 0.0914 1.0000 12.250 1.2031 0.05311 0.04684 -0.0424 0.0832 1.0000 12.500 1.2123 0.05481 0.04852 -0.0421 0.0762 1.0000 12.750 1.2220 0.05649 0.05018 -0.0420 0.0692 1.0000 13.000 1.2317 0.05819 0.05188 -0.0418 0.0608 1.0000 13.250 1.2372 0.06032 0.05393 -0.0416 0.0460 1.0000 13.500 1.2369 0.06306 0.05649 -0.0413 0.0272 1.0000 13.750 1.2446 0.06505 0.05849 -0.0412 0.0221 1.0000 14.000 1.2524 0.06707 0.06054 -0.0411 0.0197 1.0000 14.250 1.2593 0.06924 0.06275 -0.0411 0.0173 1.0000 14.500 1.2687 0.07113 0.06470 -0.0412 0.0162 1.0000 14.750 1.2777 0.07310 0.06672 -0.0413 0.0150 1.0000 15.000 1.2850 0.07529 0.06895 -0.0415 0.0142 1.0000 15.250 1.2911 0.07765 0.07136 -0.0416 0.0134 1.0000 15.500 1.2975 0.07999 0.07375 -0.0418 0.0127 1.0000 15.750 1.3055 0.08219 0.07601 -0.0421 0.0121 1.0000 16.000 1.3120 0.08461 0.07850 -0.0425 0.0115 1.0000 16.250 1.3184 0.08705 0.08100 -0.0429 0.0110 1.0000 16.500 1.3239 0.08963 0.08363 -0.0433 0.0105 1.0000 16.750 1.3272 0.09255 0.08661 -0.0438 0.0101 1.0000 17.000 1.3306 0.09548 0.08960 -0.0444 0.0097 1.0000 17.250 1.3356 0.09823 0.09243 -0.0450 0.0094 1.0000 17.500 1.3393 0.10120 0.09548 -0.0458 0.0091 1.0000 17.750 1.3433 0.10414 0.09850 -0.0465 0.0088 1.0000 18.000 1.3458 0.10735 0.10183 -0.0474 0.0086 1.0000 18.250 1.3482 0.11057 0.10512 -0.0484 0.0084 1.0000 18.500 1.3498 0.11394 0.10856 -0.0494 0.0081 1.0000 18.750 1.3512 0.11738 0.11208 -0.0506 0.0079 1.0000 19.000 1.3503 0.12121 0.11598 -0.0519 0.0077 1.0000