XFOIL Version 6.96 Calculated polar for: MH 81 13% 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 ------ -------- --------- --------- -------- -------- -------- -9.500 -0.4671 0.09411 0.09180 0.0117 0.6942 0.0119 -9.250 -0.4662 0.09011 0.08776 0.0096 0.6794 0.0119 -9.000 -0.4614 0.08733 0.08493 0.0082 0.6635 0.0121 -8.750 -0.4637 0.08280 0.08039 0.0056 0.6518 0.0121 -8.250 -0.4706 0.07430 0.07186 0.0001 0.6301 0.0123 -8.000 -0.4999 0.06659 0.06415 -0.0063 0.6246 0.0123 -7.750 -0.5105 0.05926 0.05671 -0.0109 0.6176 0.0123 -7.500 -0.5137 0.05305 0.05035 -0.0132 0.6090 0.0124 -7.250 -0.5126 0.04729 0.04438 -0.0143 0.6010 0.0127 -7.000 -0.5076 0.04196 0.03880 -0.0145 0.5920 0.0130 -6.750 -0.5206 0.03069 0.02642 -0.0126 0.5889 0.0147 -6.500 -0.4995 0.02895 0.02461 -0.0123 0.5771 0.0148 -6.250 -0.4780 0.02740 0.02292 -0.0118 0.5654 0.0150 -6.000 -0.4556 0.02598 0.02134 -0.0113 0.5539 0.0153 -5.750 -0.4436 0.01729 0.01132 -0.0076 0.5484 0.0094 -5.500 -0.4164 0.01687 0.01076 -0.0072 0.5365 0.0092 -5.250 -0.3909 0.01551 0.00929 -0.0066 0.5258 0.0090 -5.000 -0.3650 0.01443 0.00805 -0.0061 0.5153 0.0089 -4.750 -0.3385 0.01361 0.00712 -0.0056 0.5053 0.0089 -4.500 -0.3117 0.01294 0.00635 -0.0051 0.4958 0.0088 -4.250 -0.2847 0.01236 0.00567 -0.0047 0.4855 0.0088 -4.000 -0.2575 0.01187 0.00511 -0.0043 0.4758 0.0089 -3.750 -0.2300 0.01146 0.00460 -0.0039 0.4656 0.0090 -3.500 -0.2023 0.01110 0.00418 -0.0036 0.4570 0.0091 -3.000 -0.1469 0.01034 0.00329 -0.0030 0.4397 0.0096 -2.750 -0.1188 0.01011 0.00299 -0.0028 0.4304 0.0103 -2.500 -0.0903 0.00992 0.00276 -0.0026 0.4220 0.0114 -2.250 -0.0621 0.00971 0.00250 -0.0024 0.4131 0.0135 -2.000 -0.0337 0.00948 0.00228 -0.0022 0.4057 0.0201 -1.500 0.0219 0.00889 0.00195 -0.0019 0.3907 0.0951 -1.250 0.0499 0.00872 0.00187 -0.0018 0.3827 0.1358 -1.000 0.0779 0.00848 0.00180 -0.0017 0.3757 0.1883 -0.750 0.1051 0.00815 0.00174 -0.0016 0.3682 0.2781 -0.500 0.1313 0.00765 0.00169 -0.0014 0.3617 0.4240 -0.250 0.1569 0.00713 0.00165 -0.0010 0.3556 0.5783 0.000 0.1786 0.00647 0.00167 0.0004 0.3492 0.7886 0.250 0.2030 0.00633 0.00174 0.0016 0.3437 0.8720 0.500 0.2292 0.00635 0.00179 0.0024 0.3375 0.9044 0.750 0.2557 0.00644 0.00184 0.0031 0.3309 0.9253 1.000 0.2826 0.00649 0.00188 0.0037 0.3262 0.9400 1.250 0.3098 0.00657 0.00192 0.0042 0.3208 0.9524 1.500 0.3384 0.00668 0.00197 0.0044 0.3149 0.9620 1.750 0.3669 0.00674 0.00201 0.0046 0.3108 0.9711 2.000 0.4012 0.00684 0.00205 0.0035 0.3053 0.9765 2.250 0.4349 0.00700 0.00213 0.0025 0.2993 0.9835 2.500 0.4796 0.00709 0.00218 -0.0008 0.2954 0.9867 2.750 0.5212 0.00720 0.00224 -0.0035 0.2907 0.9904 3.000 0.5597 0.00735 0.00232 -0.0056 0.2851 0.9940 3.250 0.6006 0.00742 0.00236 -0.0083 0.2813 0.9963 3.500 0.6397 0.00749 0.00241 -0.0105 0.2776 0.9987 3.750 0.6737 0.00760 0.00246 -0.0118 0.2737 1.0000 4.000 0.6983 0.00774 0.00257 -0.0112 0.2694 1.0000 4.250 0.7231 0.00783 0.00265 -0.0106 0.2667 1.0000 4.500 0.7480 0.00792 0.00274 -0.0099 0.2641 1.0000 4.750 0.7727 0.00803 0.00283 -0.0093 0.2612 1.0000 5.000 0.7973 0.00816 0.00295 -0.0087 0.2581 1.0000 5.250 0.8217 0.00835 0.00310 -0.0080 0.2542 1.0000 5.500 0.8466 0.00847 0.00322 -0.0074 0.2518 1.0000 5.750 0.8718 0.00857 0.00333 -0.0069 0.2495 1.0000 6.000 0.8971 0.00870 0.00346 -0.0064 0.2469 1.0000 6.250 0.9224 0.00885 0.00360 -0.0059 0.2442 1.0000 6.500 0.9477 0.00905 0.00377 -0.0055 0.2408 1.0000 6.750 0.9731 0.00925 0.00396 -0.0051 0.2377 1.0000 7.000 0.9994 0.00936 0.00410 -0.0048 0.2357 1.0000 7.250 1.0258 0.00950 0.00425 -0.0045 0.2334 1.0000 7.500 1.0521 0.00966 0.00442 -0.0043 0.2308 1.0000 7.750 1.0784 0.00986 0.00461 -0.0041 0.2277 1.0000 8.000 1.1041 0.01015 0.00488 -0.0039 0.2237 1.0000 8.250 1.1312 0.01027 0.00504 -0.0039 0.2222 1.0000 8.500 1.1581 0.01042 0.00522 -0.0038 0.2200 1.0000 8.750 1.1849 0.01059 0.00541 -0.0037 0.2172 1.0000 9.000 1.2112 0.01081 0.00563 -0.0037 0.2141 1.0000 9.250 1.2368 0.01112 0.00593 -0.0036 0.2104 1.0000 9.500 1.2635 0.01130 0.00615 -0.0035 0.2081 1.0000 9.750 1.2902 0.01147 0.00636 -0.0035 0.2057 1.0000 10.000 1.3164 0.01168 0.00659 -0.0035 0.2026 1.0000 10.250 1.3421 0.01195 0.00687 -0.0034 0.1993 1.0000 10.500 1.3669 0.01230 0.00721 -0.0032 0.1955 1.0000 10.750 1.3933 0.01247 0.00745 -0.0032 0.1932 1.0000 11.000 1.4190 0.01270 0.00771 -0.0031 0.1901 1.0000 11.250 1.4439 0.01300 0.00802 -0.0030 0.1866 1.0000 11.500 1.4673 0.01343 0.00845 -0.0028 0.1825 1.0000 11.750 1.4930 0.01363 0.00872 -0.0027 0.1801 1.0000 12.000 1.5175 0.01392 0.00904 -0.0026 0.1767 1.0000 12.250 1.5406 0.01431 0.00944 -0.0023 0.1727 1.0000 12.500 1.5629 0.01474 0.00990 -0.0019 0.1689 1.0000 12.750 1.5867 0.01504 0.01026 -0.0017 0.1659 1.0000 13.000 1.6086 0.01545 0.01070 -0.0013 0.1619 1.0000 13.250 1.6274 0.01605 0.01130 -0.0007 0.1570 1.0000 13.500 1.6495 0.01639 0.01170 -0.0003 0.1532 1.0000 13.750 1.6671 0.01700 0.01231 0.0004 0.1475 1.0000 14.000 1.6836 0.01761 0.01295 0.0013 0.1422 1.0000 14.250 1.6961 0.01833 0.01369 0.0026 0.1364 1.0000 14.500 1.6991 0.01927 0.01465 0.0051 0.1311 1.0000 14.750 1.7054 0.02026 0.01570 0.0066 0.1280 1.0000 15.000 1.7049 0.02193 0.01739 0.0079 0.1227 1.0000 15.250 1.7069 0.02370 0.01920 0.0085 0.1168 1.0000 15.500 1.7005 0.02641 0.02192 0.0088 0.1102 1.0000 15.750 1.7038 0.02843 0.02403 0.0088 0.1079 1.0000 16.000 1.6944 0.03182 0.02744 0.0084 0.1017 1.0000 16.250 1.6855 0.03528 0.03096 0.0078 0.0974 1.0000 16.500 1.6750 0.03904 0.03479 0.0070 0.0936 1.0000 16.750 1.6568 0.04374 0.03956 0.0058 0.0902 1.0000 17.000 1.6386 0.04859 0.04448 0.0045 0.0861 1.0000 17.250 1.6149 0.05421 0.05017 0.0028 0.0825 1.0000 17.500 1.5972 0.05935 0.05540 0.0010 0.0811 1.0000 17.750 1.5766 0.06511 0.06125 -0.0011 0.0784 1.0000 18.000 1.5563 0.07097 0.06720 -0.0034 0.0759 1.0000 18.250 1.5355 0.07708 0.07338 -0.0059 0.0737 1.0000 18.500 1.5107 0.08393 0.08031 -0.0089 0.0711 1.0000 18.750 1.4963 0.08944 0.08591 -0.0114 0.0697 1.0000