XFOIL Version 6.96 Calculated polar for: NACA 0008 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 ------ -------- --------- --------- -------- -------- -------- -9.750 -0.7159 0.09334 0.08645 0.0017 1.0000 0.0512 -9.500 -0.7263 0.08537 0.07852 -0.0047 1.0000 0.0504 -9.250 -0.7428 0.07833 0.07146 -0.0100 1.0000 0.0495 -9.000 -0.7590 0.07249 0.06552 -0.0126 1.0000 0.0490 -8.750 -0.7702 0.06691 0.05974 -0.0143 1.0000 0.0488 -8.500 -0.7765 0.06165 0.05420 -0.0151 1.0000 0.0490 -8.250 -0.7778 0.05665 0.04882 -0.0152 1.0000 0.0493 -8.000 -0.7743 0.05197 0.04368 -0.0148 1.0000 0.0501 -7.750 -0.7665 0.04777 0.03894 -0.0141 1.0000 0.0522 -7.500 -0.7556 0.04383 0.03422 -0.0131 1.0000 0.0552 -7.250 -0.7397 0.04054 0.03065 -0.0124 1.0000 0.0579 -7.000 -0.7207 0.03779 0.02759 -0.0115 1.0000 0.0608 -6.500 -0.6786 0.03305 0.02200 -0.0098 1.0000 0.0716 -6.250 -0.6552 0.03106 0.01981 -0.0090 1.0000 0.0764 -6.000 -0.6318 0.02939 0.01787 -0.0083 1.0000 0.0848 -5.750 -0.6077 0.02780 0.01617 -0.0075 1.0000 0.0913 -5.500 -0.5830 0.02627 0.01444 -0.0065 1.0000 0.0979 -5.250 -0.5596 0.02494 0.01300 -0.0056 1.0000 0.1068 -5.000 -0.5365 0.02373 0.01175 -0.0048 1.0000 0.1225 -4.750 -0.5138 0.02245 0.01060 -0.0041 1.0000 0.1485 -4.500 -0.4914 0.02105 0.00945 -0.0034 1.0000 0.1926 -4.250 -0.4710 0.01971 0.00860 -0.0026 1.0000 0.2797 -4.000 -0.4535 0.01856 0.00809 -0.0009 1.0000 0.4032 -3.750 -0.4364 0.01772 0.00782 0.0017 1.0000 0.5239 -3.500 -0.4176 0.01718 0.00764 0.0045 1.0000 0.6200 -3.250 -0.3967 0.01685 0.00752 0.0073 1.0000 0.7031 -3.000 -0.3717 0.01671 0.00743 0.0095 1.0000 0.7747 -2.750 -0.3403 0.01668 0.00732 0.0103 1.0000 0.8347 -2.500 -0.2999 0.01670 0.00713 0.0090 1.0000 0.8838 -2.250 -0.2537 0.01669 0.00688 0.0060 1.0000 0.9244 -2.000 -0.1993 0.01660 0.00653 0.0008 1.0000 0.9563 -1.750 -0.1431 0.01640 0.00607 -0.0052 1.0000 0.9836 -1.500 -0.0988 0.01611 0.00563 -0.0093 1.0000 1.0000 -1.250 -0.0818 0.01588 0.00532 -0.0081 1.0000 1.0000 -1.000 -0.0649 0.01571 0.00508 -0.0067 1.0000 1.0000 -0.750 -0.0483 0.01557 0.00491 -0.0052 1.0000 1.0000 -0.500 -0.0319 0.01548 0.00479 -0.0035 1.0000 1.0000 -0.250 -0.0158 0.01543 0.00471 -0.0018 1.0000 1.0000 0.000 0.0000 0.01541 0.00469 0.0000 1.0000 1.0000 0.250 0.0158 0.01543 0.00471 0.0018 1.0000 1.0000 0.500 0.0319 0.01548 0.00479 0.0035 1.0000 1.0000 0.750 0.0483 0.01557 0.00491 0.0052 1.0000 1.0000 1.000 0.0649 0.01570 0.00508 0.0067 1.0000 1.0000 1.250 0.0818 0.01588 0.00532 0.0081 1.0000 1.0000 1.500 0.0988 0.01611 0.00563 0.0093 1.0000 1.0000 1.750 0.1431 0.01640 0.00607 0.0052 0.9836 1.0000 2.000 0.1993 0.01660 0.00653 -0.0008 0.9563 1.0000 2.250 0.2537 0.01669 0.00688 -0.0060 0.9244 1.0000 2.500 0.2999 0.01670 0.00713 -0.0090 0.8839 1.0000 2.750 0.3403 0.01668 0.00732 -0.0103 0.8348 1.0000 3.000 0.3717 0.01671 0.00743 -0.0095 0.7747 1.0000 3.250 0.3967 0.01685 0.00752 -0.0073 0.7031 1.0000 3.500 0.4176 0.01718 0.00764 -0.0045 0.6200 1.0000 3.750 0.4364 0.01772 0.00782 -0.0017 0.5239 1.0000 4.000 0.4535 0.01856 0.00809 0.0009 0.4033 1.0000 4.250 0.4710 0.01971 0.00860 0.0026 0.2797 1.0000 4.500 0.4915 0.02105 0.00945 0.0034 0.1926 1.0000 4.750 0.5139 0.02245 0.01060 0.0041 0.1485 1.0000 5.000 0.5365 0.02373 0.01175 0.0048 0.1225 1.0000 5.250 0.5597 0.02494 0.01300 0.0056 0.1068 1.0000 5.500 0.5830 0.02627 0.01444 0.0065 0.0979 1.0000 5.750 0.6077 0.02780 0.01617 0.0075 0.0913 1.0000 6.000 0.6318 0.02939 0.01787 0.0083 0.0848 1.0000 6.250 0.6553 0.03106 0.01981 0.0090 0.0764 1.0000 6.500 0.6786 0.03305 0.02200 0.0098 0.0716 1.0000 7.000 0.7207 0.03779 0.02759 0.0115 0.0608 1.0000 7.250 0.7397 0.04054 0.03065 0.0124 0.0579 1.0000 7.500 0.7556 0.04383 0.03422 0.0131 0.0552 1.0000 7.750 0.7665 0.04777 0.03894 0.0141 0.0522 1.0000 8.000 0.7743 0.05197 0.04368 0.0148 0.0501 1.0000 8.250 0.7778 0.05666 0.04882 0.0152 0.0493 1.0000 8.500 0.7765 0.06166 0.05420 0.0151 0.0490 1.0000 8.750 0.7703 0.06692 0.05975 0.0143 0.0488 1.0000 9.000 0.7591 0.07250 0.06553 0.0126 0.0490 1.0000 9.250 0.7430 0.07836 0.07149 0.0100 0.0495 1.0000 9.500 0.7266 0.08542 0.07856 0.0046 0.0504 1.0000 9.750 0.7163 0.09339 0.08650 -0.0018 0.0512 1.0000