XFOIL Version 6.96 Calculated polar for: dh4009sm 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 ------ -------- --------- --------- -------- -------- -------- -9.250 -0.6673 0.08261 0.08102 -0.0146 1.0000 0.0063 -9.000 -0.6831 0.07690 0.07527 -0.0188 1.0000 0.0062 -8.750 -0.7001 0.07293 0.07124 -0.0188 1.0000 0.0062 -8.500 -0.7072 0.06864 0.06687 -0.0189 1.0000 0.0063 -8.250 -0.7103 0.06456 0.06270 -0.0185 1.0000 0.0064 -8.000 -0.7103 0.06058 0.05860 -0.0178 1.0000 0.0067 -7.750 -0.7071 0.05669 0.05458 -0.0168 1.0000 0.0070 -7.500 -0.6963 0.05309 0.05082 -0.0153 1.0000 0.0080 -6.000 -0.6228 0.03560 0.03221 -0.0033 1.0000 0.0088 -5.750 -0.6092 0.03306 0.02946 -0.0010 1.0000 0.0088 -5.500 -0.6092 0.02618 0.02213 0.0030 1.0000 0.0095 -5.250 -0.5941 0.02425 0.02005 0.0050 1.0000 0.0098 -5.000 -0.5654 0.02240 0.01805 0.0041 0.9990 0.0102 -4.750 -0.5340 0.02066 0.01614 0.0028 0.9975 0.0107 -4.500 -0.5015 0.01906 0.01435 0.0016 0.9958 0.0115 -4.250 -0.4698 0.01763 0.01276 0.0008 0.9930 0.0125 -4.000 -0.4386 0.01702 0.01205 0.0002 0.9862 0.0141 -3.500 -0.3803 0.01204 0.00671 0.0007 0.9743 0.0112 -3.250 -0.3484 0.01087 0.00549 -0.0001 0.9694 0.0118 -3.000 -0.3151 0.01001 0.00458 -0.0014 0.9637 0.0123 -2.750 -0.2795 0.00921 0.00373 -0.0034 0.9575 0.0125 -2.500 -0.2394 0.00862 0.00310 -0.0064 0.9527 0.0133 -2.250 -0.1982 0.00797 0.00235 -0.0097 0.9450 0.0130 -2.000 -0.1514 0.00753 0.00181 -0.0143 0.9391 0.0134 -1.750 -0.1073 0.00720 0.00137 -0.0182 0.9282 0.0198 -1.500 -0.0918 0.00466 0.00086 -0.0172 0.9070 0.6352 -1.250 -0.0647 0.00449 0.00087 -0.0171 0.8916 0.7059 -1.000 -0.0391 0.00446 0.00090 -0.0166 0.8770 0.7501 -0.750 -0.0131 0.00447 0.00091 -0.0161 0.8615 0.7687 -0.500 0.0133 0.00452 0.00090 -0.0158 0.8463 0.7781 -0.250 0.0397 0.00454 0.00089 -0.0155 0.8334 0.7846 0.000 0.0664 0.00457 0.00088 -0.0153 0.8230 0.7914 0.250 0.0930 0.00458 0.00090 -0.0151 0.8132 0.7979 0.750 0.1456 0.00462 0.00093 -0.0145 0.7913 0.8114 1.000 0.1704 0.00469 0.00094 -0.0138 0.7717 0.8188 1.250 0.1949 0.00473 0.00096 -0.0130 0.7480 0.8255 1.500 0.2183 0.00483 0.00097 -0.0120 0.7135 0.8331 1.750 0.2417 0.00494 0.00100 -0.0110 0.6757 0.8403 2.000 0.2647 0.00511 0.00104 -0.0100 0.6241 0.8480 2.250 0.2824 0.00563 0.00114 -0.0080 0.4972 0.8563 2.500 0.2969 0.00659 0.00141 -0.0056 0.2987 0.8650 2.750 0.3119 0.00764 0.00173 -0.0034 0.0952 0.8747 3.000 0.3342 0.00806 0.00197 -0.0024 0.0377 0.8837 3.250 0.3589 0.00829 0.00219 -0.0018 0.0260 0.8928 3.500 0.3833 0.00854 0.00251 -0.0011 0.0209 0.9029 3.750 0.4083 0.00874 0.00278 -0.0005 0.0180 0.9135 4.000 0.4317 0.00917 0.00330 0.0004 0.0147 0.9252 4.250 0.4540 0.00983 0.00411 0.0016 0.0132 0.9387 4.500 0.4803 0.01037 0.00475 0.0018 0.0127 0.9517 4.750 0.5094 0.01115 0.00563 0.0013 0.0123 0.9628 5.000 0.5412 0.01187 0.00644 0.0002 0.0117 0.9719 5.250 0.5738 0.01298 0.00765 -0.0011 0.0114 0.9774 5.500 0.6053 0.01421 0.00899 -0.0021 0.0111 0.9831 5.750 0.6369 0.01551 0.01043 -0.0032 0.0107 0.9876 6.000 0.6674 0.01666 0.01170 -0.0041 0.0101 0.9930 6.250 0.6977 0.01790 0.01308 -0.0050 0.0095 0.9974 7.250 0.7270 0.03676 0.03373 0.0106 0.0121 1.0000 7.500 0.7398 0.03925 0.03641 0.0128 0.0109 1.0000 7.750 0.7491 0.04194 0.03928 0.0149 0.0102 1.0000 8.000 0.7575 0.04444 0.04193 0.0167 0.0097 1.0000 8.250 0.7654 0.04659 0.04420 0.0182 0.0093 1.0000 8.500 0.7718 0.04865 0.04637 0.0196 0.0090 1.0000 8.750 0.7723 0.05150 0.04935 0.0212 0.0088 1.0000 9.000 0.7619 0.05576 0.05377 0.0231 0.0085 1.0000