XFOIL Version 6.96 Calculated polar for: M6 (65%) 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -10.000 -0.9063 0.03088 0.02816 -0.0222 1.0000 0.0056 -9.750 -0.9166 0.02494 0.02157 -0.0180 1.0000 0.0057 -9.500 -0.9063 0.02266 0.01897 -0.0156 1.0000 0.0057 -9.250 -0.8922 0.02099 0.01705 -0.0136 1.0000 0.0058 -9.000 -0.8771 0.01948 0.01530 -0.0116 1.0000 0.0059 -8.750 -0.8596 0.01835 0.01397 -0.0100 1.0000 0.0059 -8.500 -0.8418 0.01726 0.01270 -0.0083 1.0000 0.0059 -8.250 -0.8229 0.01635 0.01163 -0.0067 1.0000 0.0060 -8.000 -0.8040 0.01545 0.01059 -0.0051 1.0000 0.0060 -7.750 -0.7850 0.01459 0.00956 -0.0034 1.0000 0.0061 -7.500 -0.7651 0.01390 0.00876 -0.0019 1.0000 0.0061 -7.250 -0.7389 0.01325 0.00801 -0.0018 0.9989 0.0062 -7.000 -0.7084 0.01261 0.00727 -0.0026 0.9959 0.0063 -6.750 -0.6791 0.01208 0.00668 -0.0031 0.9918 0.0064 -6.500 -0.6489 0.01159 0.00613 -0.0038 0.9874 0.0065 -6.250 -0.6192 0.01116 0.00564 -0.0043 0.9816 0.0067 -5.750 -0.5529 0.01036 0.00475 -0.0069 0.9683 0.0070 -5.500 -0.5165 0.00999 0.00434 -0.0088 0.9581 0.0071 -5.250 -0.4784 0.00965 0.00395 -0.0112 0.9419 0.0073 -5.000 -0.4444 0.00939 0.00362 -0.0126 0.9169 0.0075 -4.750 -0.4171 0.00925 0.00338 -0.0124 0.8877 0.0078 -4.500 -0.3923 0.00910 0.00312 -0.0117 0.8609 0.0085 -4.250 -0.3678 0.00898 0.00285 -0.0109 0.8362 0.0094 -4.000 -0.3429 0.00887 0.00263 -0.0101 0.8137 0.0100 -3.750 -0.3178 0.00880 0.00247 -0.0095 0.7932 0.0106 -3.500 -0.2924 0.00872 0.00232 -0.0089 0.7748 0.0108 -3.250 -0.2671 0.00860 0.00212 -0.0083 0.7574 0.0113 -3.000 -0.2416 0.00850 0.00195 -0.0078 0.7408 0.0117 -2.750 -0.2160 0.00839 0.00180 -0.0073 0.7253 0.0126 -2.500 -0.1902 0.00830 0.00166 -0.0068 0.7110 0.0130 -2.250 -0.1643 0.00822 0.00153 -0.0063 0.6969 0.0134 -2.000 -0.1383 0.00815 0.00142 -0.0059 0.6833 0.0138 -1.750 -0.1121 0.00809 0.00131 -0.0055 0.6707 0.0139 -1.500 -0.0859 0.00803 0.00122 -0.0051 0.6585 0.0149 -1.250 -0.0597 0.00796 0.00113 -0.0047 0.6461 0.0167 -1.000 -0.0336 0.00787 0.00105 -0.0043 0.6348 0.0236 -0.750 -0.0072 0.00782 0.00099 -0.0040 0.6238 0.0294 -0.500 0.0190 0.00776 0.00093 -0.0036 0.6134 0.0357 -0.250 0.0450 0.00766 0.00087 -0.0032 0.6022 0.0584 0.000 0.0710 0.00757 0.00083 -0.0028 0.5918 0.0824 0.250 0.0969 0.00747 0.00080 -0.0024 0.5816 0.1150 0.500 0.1226 0.00737 0.00078 -0.0019 0.5706 0.1503 0.750 0.1477 0.00725 0.00077 -0.0014 0.5562 0.2034 1.000 0.1710 0.00700 0.00076 -0.0006 0.5374 0.3058 1.250 0.1666 0.00519 0.00069 0.0062 0.5245 0.8473 1.500 0.2420 0.00523 0.00096 -0.0044 0.5007 0.9483 1.750 0.2752 0.00543 0.00110 -0.0055 0.4831 0.9610 2.000 0.3099 0.00567 0.00126 -0.0069 0.4609 0.9698 2.250 0.3444 0.00591 0.00144 -0.0083 0.4416 0.9773 2.500 0.3753 0.00607 0.00150 -0.0091 0.4138 0.9783 2.750 0.4038 0.00646 0.00160 -0.0095 0.3431 0.9796 3.000 0.4316 0.00686 0.00174 -0.0098 0.2768 0.9813 3.250 0.4574 0.00740 0.00194 -0.0097 0.1970 0.9834 3.500 0.4808 0.00789 0.00216 -0.0090 0.1338 0.9861 3.750 0.5096 0.00842 0.00240 -0.0096 0.0701 0.9870 4.000 0.5392 0.00872 0.00260 -0.0102 0.0441 0.9879 4.250 0.5688 0.00899 0.00278 -0.0108 0.0286 0.9889 4.500 0.5982 0.00925 0.00299 -0.0113 0.0187 0.9900 4.750 0.6274 0.00946 0.00319 -0.0118 0.0156 0.9913 5.000 0.6558 0.00970 0.00342 -0.0121 0.0132 0.9925 5.250 0.6838 0.00997 0.00370 -0.0122 0.0121 0.9938 5.500 0.7120 0.01020 0.00396 -0.0125 0.0117 0.9949 5.750 0.7417 0.01045 0.00423 -0.0131 0.0114 0.9956 6.000 0.7708 0.01072 0.00453 -0.0136 0.0111 0.9965 6.250 0.7994 0.01102 0.00486 -0.0140 0.0106 0.9974 6.500 0.8280 0.01133 0.00521 -0.0144 0.0102 0.9983 6.750 0.8564 0.01170 0.00562 -0.0148 0.0099 0.9992 7.000 0.8845 0.01209 0.00606 -0.0151 0.0097 0.9999 7.250 0.9069 0.01249 0.00651 -0.0142 0.0095 1.0000 7.500 0.9274 0.01294 0.00700 -0.0130 0.0093 1.0000 7.750 0.9473 0.01344 0.00756 -0.0116 0.0090 1.0000 8.000 0.9638 0.01431 0.00852 -0.0097 0.0084 1.0000 8.250 0.9824 0.01493 0.00922 -0.0081 0.0083 1.0000 8.500 1.0021 0.01541 0.00975 -0.0068 0.0083 1.0000 8.750 1.0237 0.01565 0.01002 -0.0058 0.0081 1.0000 9.000 1.0426 0.01619 0.01063 -0.0044 0.0081 1.0000 9.250 1.0618 0.01668 0.01117 -0.0030 0.0079 1.0000 9.500 1.0816 0.01708 0.01163 -0.0017 0.0077 1.0000 9.750 1.0993 0.01769 0.01232 -0.0002 0.0076 1.0000 10.000 1.1179 0.01818 0.01287 0.0012 0.0073 1.0000 10.250 1.1349 0.01881 0.01358 0.0029 0.0072 1.0000 10.500 1.1518 0.01942 0.01425 0.0045 0.0070 1.0000 10.750 1.1691 0.01996 0.01486 0.0060 0.0068 1.0000 11.000 1.1844 0.02065 0.01563 0.0078 0.0067 1.0000 11.250 1.2012 0.02116 0.01621 0.0093 0.0065 1.0000 11.500 1.2149 0.02192 0.01706 0.0113 0.0064 1.0000 11.750 1.2299 0.02251 0.01770 0.0130 0.0063 1.0000 12.000 1.2468 0.02288 0.01809 0.0144 0.0060 1.0000 12.250 1.2605 0.02349 0.01875 0.0162 0.0058 1.0000 12.500 1.2679 0.02442 0.01978 0.0190 0.0057 1.0000 12.750 1.2694 0.02540 0.02085 0.0226 0.0056 1.0000 13.000 1.2703 0.02660 0.02217 0.0259 0.0055 1.0000 13.250 1.2825 0.02717 0.02280 0.0275 0.0054 1.0000 13.500 1.2868 0.02842 0.02416 0.0295 0.0054 1.0000 13.750 1.2870 0.03015 0.02602 0.0313 0.0053 1.0000 14.000 1.2968 0.03120 0.02717 0.0323 0.0052 1.0000 14.250 1.2961 0.03335 0.02946 0.0332 0.0051 1.0000 14.500 1.3003 0.03519 0.03141 0.0337 0.0049 1.0000 14.750 1.3030 0.03732 0.03365 0.0338 0.0047 1.0000 15.000 1.3052 0.03966 0.03610 0.0336 0.0044 1.0000 15.250 1.3037 0.04258 0.03915 0.0330 0.0043 1.0000 15.500 1.2960 0.04645 0.04316 0.0319 0.0043 1.0000 15.750 1.2984 0.04918 0.04598 0.0309 0.0039 1.0000 16.000 1.2977 0.05239 0.04927 0.0296 0.0037 1.0000 16.250 1.2859 0.05737 0.05439 0.0273 0.0038 1.0000 16.500 1.2929 0.05968 0.05671 0.0263 0.0034 1.0000