XFOIL Version 6.96 Calculated polar for: S9032 (9%) 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -8.750 -0.7417 0.07647 0.06948 -0.0083 1.0000 0.1561 -8.500 -0.7470 0.07074 0.06369 -0.0099 1.0000 0.1544 -8.250 -0.7561 0.06463 0.05744 -0.0117 1.0000 0.1524 -8.000 -0.7637 0.05855 0.05108 -0.0130 1.0000 0.1512 -7.750 -0.7657 0.05295 0.04508 -0.0136 1.0000 0.1512 -7.500 -0.7620 0.04781 0.03944 -0.0134 1.0000 0.1523 -7.250 -0.7542 0.04319 0.03416 -0.0128 1.0000 0.1552 -7.000 -0.7362 0.04062 0.03150 -0.0118 1.0000 0.1649 -6.750 -0.7206 0.03745 0.02788 -0.0108 1.0000 0.1744 -6.500 -0.7023 0.03468 0.02457 -0.0097 1.0000 0.1854 -6.250 -0.6812 0.03274 0.02264 -0.0087 1.0000 0.2017 -6.000 -0.6591 0.03073 0.02053 -0.0076 1.0000 0.2177 -5.750 -0.6374 0.02914 0.01883 -0.0065 1.0000 0.2395 -5.500 -0.6145 0.02734 0.01698 -0.0054 1.0000 0.2609 -5.250 -0.5925 0.02597 0.01564 -0.0041 1.0000 0.2894 -5.000 -0.5701 0.02466 0.01443 -0.0027 1.0000 0.3210 -4.750 -0.5485 0.02350 0.01335 -0.0012 1.0000 0.3596 -4.500 -0.5273 0.02247 0.01249 0.0005 1.0000 0.4027 -4.250 -0.5064 0.02157 0.01184 0.0026 1.0000 0.4494 -4.000 -0.4862 0.02077 0.01126 0.0049 1.0000 0.5011 -3.750 -0.4662 0.02011 0.01086 0.0075 1.0000 0.5538 -3.500 -0.4467 0.01955 0.01049 0.0105 1.0000 0.6087 -3.250 -0.4287 0.01910 0.01023 0.0140 1.0000 0.6644 -3.000 -0.4109 0.01876 0.01006 0.0179 1.0000 0.7192 -2.750 -0.3916 0.01854 0.00997 0.0220 1.0000 0.7739 -2.500 -0.3637 0.01850 0.00995 0.0247 1.0000 0.8304 -2.250 -0.3021 0.01885 0.01010 0.0214 1.0000 0.8896 -2.000 -0.1824 0.01912 0.00985 0.0059 1.0000 0.9460 -1.750 -0.0670 0.01815 0.00850 -0.0117 1.0000 0.9960 -1.500 -0.0492 0.01739 0.00770 -0.0126 1.0000 1.0000 -1.250 -0.0407 0.01684 0.00714 -0.0113 1.0000 1.0000 -1.000 -0.0324 0.01640 0.00670 -0.0096 1.0000 1.0000 -0.750 -0.0245 0.01607 0.00638 -0.0074 1.0000 1.0000 -0.500 -0.0167 0.01584 0.00615 -0.0050 1.0000 1.0000 -0.250 -0.0087 0.01571 0.00602 -0.0025 1.0000 1.0000 0.000 0.0000 0.01566 0.00598 0.0000 1.0000 1.0000 0.250 0.0087 0.01571 0.00602 0.0025 1.0000 1.0000 0.500 0.0167 0.01584 0.00615 0.0050 1.0000 1.0000 0.750 0.0245 0.01607 0.00638 0.0074 1.0000 1.0000 1.000 0.0324 0.01640 0.00670 0.0096 1.0000 1.0000 1.250 0.0407 0.01684 0.00713 0.0113 1.0000 1.0000 1.500 0.0492 0.01739 0.00770 0.0126 1.0000 1.0000 1.750 0.0670 0.01815 0.00850 0.0117 0.9960 1.0000 2.000 0.1822 0.01912 0.00985 -0.0059 0.9460 1.0000 2.250 0.3021 0.01886 0.01010 -0.0214 0.8895 1.0000 2.500 0.3638 0.01850 0.00995 -0.0247 0.8303 1.0000 2.750 0.3918 0.01854 0.00998 -0.0220 0.7737 1.0000 3.000 0.4111 0.01876 0.01006 -0.0179 0.7190 1.0000 3.250 0.4290 0.01910 0.01023 -0.0140 0.6643 1.0000 3.500 0.4470 0.01954 0.01049 -0.0105 0.6085 1.0000 3.750 0.4664 0.02011 0.01086 -0.0076 0.5535 1.0000 4.000 0.4864 0.02078 0.01127 -0.0049 0.5009 1.0000 4.250 0.5066 0.02157 0.01184 -0.0026 0.4492 1.0000 4.500 0.5276 0.02248 0.01249 -0.0006 0.4026 1.0000 4.750 0.5487 0.02349 0.01335 0.0012 0.3595 1.0000 5.000 0.5703 0.02466 0.01443 0.0027 0.3209 1.0000 5.250 0.5926 0.02597 0.01564 0.0041 0.2893 1.0000 5.500 0.6147 0.02734 0.01698 0.0053 0.2609 1.0000 5.750 0.6375 0.02914 0.01883 0.0065 0.2395 1.0000 6.000 0.6591 0.03072 0.02053 0.0076 0.2176 1.0000 6.250 0.6812 0.03274 0.02265 0.0087 0.2016 1.0000 6.500 0.7023 0.03467 0.02457 0.0097 0.1854 1.0000 6.750 0.7205 0.03744 0.02787 0.0109 0.1743 1.0000 7.000 0.7360 0.04061 0.03149 0.0119 0.1649 1.0000 7.250 0.7540 0.04316 0.03413 0.0128 0.1552 1.0000 7.500 0.7617 0.04779 0.03941 0.0135 0.1523 1.0000 7.750 0.7654 0.05290 0.04503 0.0137 0.1513 1.0000 8.000 0.7633 0.05848 0.05101 0.0132 0.1511 1.0000 8.250 0.7558 0.06458 0.05738 0.0119 0.1525 1.0000 8.500 0.7465 0.07068 0.06363 0.0101 0.1544 1.0000 8.750 0.7405 0.07647 0.06948 0.0083 0.1560 1.0000