XFOIL Version 6.96 Calculated polar for: R140 12.04% (smoothed) 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 ------ -------- --------- --------- -------- -------- -------- -12.000 -0.4585 0.09829 0.09676 -0.0301 1.0000 0.0085 -11.750 -0.4683 0.09119 0.08967 -0.0326 1.0000 0.0085 -9.000 -0.8454 0.03044 0.02693 -0.0177 1.0000 0.0057 -8.500 -0.8263 0.02485 0.02072 -0.0132 0.9973 0.0056 -8.250 -0.8019 0.02240 0.01800 -0.0138 0.9948 0.0058 -8.000 -0.7785 0.01981 0.01509 -0.0136 0.9918 0.0057 -7.750 -0.7498 0.01910 0.01434 -0.0146 0.9886 0.0062 -7.500 -0.7204 0.01796 0.01306 -0.0156 0.9859 0.0065 -7.250 -0.6902 0.01664 0.01162 -0.0166 0.9837 0.0068 -7.000 -0.6626 0.01536 0.01021 -0.0170 0.9800 0.0072 -6.750 -0.6354 0.01424 0.00899 -0.0172 0.9753 0.0075 -6.500 -0.6034 0.01350 0.00817 -0.0185 0.9721 0.0081 -6.250 -0.5684 0.01298 0.00759 -0.0204 0.9693 0.0085 -6.000 -0.5464 0.01146 0.00589 -0.0198 0.9607 0.0093 -5.750 -0.5155 0.01073 0.00508 -0.0209 0.9546 0.0102 -5.500 -0.4879 0.01032 0.00463 -0.0211 0.9449 0.0117 -5.250 -0.4605 0.01004 0.00430 -0.0213 0.9351 0.0130 -5.000 -0.4361 0.00962 0.00378 -0.0206 0.9241 0.0141 -4.750 -0.4134 0.00922 0.00329 -0.0196 0.9122 0.0175 -4.500 -0.3901 0.00894 0.00294 -0.0188 0.8999 0.0237 -4.250 -0.3699 0.00847 0.00263 -0.0174 0.8865 0.0641 -4.000 -0.3499 0.00801 0.00236 -0.0160 0.8723 0.1216 -3.750 -0.3311 0.00747 0.00207 -0.0144 0.8569 0.2011 -3.500 -0.3199 0.00644 0.00168 -0.0116 0.8394 0.3792 -3.250 -0.3022 0.00593 0.00148 -0.0097 0.8223 0.4792 -3.000 -0.2814 0.00568 0.00136 -0.0084 0.8053 0.5385 -2.750 -0.2591 0.00556 0.00131 -0.0073 0.7890 0.5844 -2.500 -0.2347 0.00553 0.00126 -0.0066 0.7735 0.6088 -2.250 -0.2092 0.00553 0.00119 -0.0061 0.7593 0.6221 -1.750 -0.1585 0.00550 0.00111 -0.0052 0.7343 0.6508 -1.500 -0.1327 0.00549 0.00107 -0.0049 0.7231 0.6634 -1.250 -0.1066 0.00548 0.00103 -0.0046 0.7132 0.6720 -0.750 -0.0540 0.00546 0.00097 -0.0041 0.6951 0.6907 -0.500 -0.0280 0.00544 0.00095 -0.0038 0.6870 0.7005 -0.250 -0.0017 0.00543 0.00094 -0.0036 0.6789 0.7096 0.000 0.0247 0.00541 0.00093 -0.0034 0.6719 0.7199 0.500 0.0769 0.00538 0.00095 -0.0029 0.6584 0.7459 0.750 0.1028 0.00536 0.00098 -0.0025 0.6516 0.7615 1.000 0.1285 0.00536 0.00102 -0.0021 0.6458 0.7783 1.250 0.1545 0.00534 0.00106 -0.0018 0.6389 0.7952 1.500 0.1802 0.00536 0.00111 -0.0014 0.6314 0.8112 1.750 0.2061 0.00537 0.00115 -0.0010 0.6226 0.8257 2.000 0.2319 0.00538 0.00119 -0.0007 0.6119 0.8391 2.250 0.2578 0.00540 0.00124 -0.0003 0.6029 0.8513 2.500 0.2836 0.00544 0.00130 0.0001 0.5918 0.8631 2.750 0.3101 0.00545 0.00137 0.0003 0.5827 0.8744 3.250 0.3616 0.00557 0.00150 0.0010 0.5480 0.8968 3.500 0.3875 0.00567 0.00159 0.0014 0.5229 0.9077 3.750 0.4136 0.00582 0.00170 0.0016 0.4908 0.9184 4.000 0.4354 0.00632 0.00189 0.0026 0.3997 0.9303 4.250 0.4499 0.00770 0.00245 0.0044 0.2014 0.9438 4.500 0.4712 0.00881 0.00300 0.0049 0.0626 0.9550 4.750 0.5029 0.00957 0.00358 0.0036 0.0160 0.9603 5.000 0.5342 0.00992 0.00398 0.0026 0.0139 0.9663 5.250 0.5658 0.01032 0.00441 0.0014 0.0118 0.9706 5.500 0.5953 0.01123 0.00545 0.0006 0.0098 0.9739 5.750 0.6254 0.01173 0.00600 -0.0002 0.0093 0.9778 6.000 0.6514 0.01234 0.00669 -0.0002 0.0089 0.9831 6.250 0.6825 0.01306 0.00746 -0.0014 0.0081 0.9851 6.500 0.7121 0.01390 0.00837 -0.0023 0.0077 0.9879 6.750 0.7425 0.01445 0.00894 -0.0034 0.0069 0.9909 7.000 0.7687 0.01545 0.00999 -0.0037 0.0066 0.9941 7.250 0.7966 0.01685 0.01149 -0.0045 0.0064 0.9961 7.500 0.8229 0.01896 0.01373 -0.0049 0.0062 0.9978 7.750 0.8492 0.02141 0.01644 -0.0052 0.0059 0.9992 8.000 0.8712 0.02280 0.01800 -0.0046 0.0058 1.0000 8.250 0.8834 0.02310 0.01840 -0.0018 0.0055 1.0000 8.500 0.8924 0.02504 0.02057 0.0015 0.0053 1.0000 8.750 0.8967 0.02777 0.02360 0.0055 0.0051 1.0000 9.000 0.8920 0.03135 0.02752 0.0105 0.0055 1.0000 12.250 0.6754 0.09174 0.09013 0.0260 0.0070 1.0000 12.500 0.6523 0.10698 0.10537 0.0171 0.0071 1.0000