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 = 0.500 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -10.750 -0.4991 0.07284 0.07074 -0.0430 1.0000 0.0180 -10.500 -0.5294 0.06370 0.06154 -0.0481 1.0000 0.0170 -10.250 -0.5599 0.05666 0.05440 -0.0511 1.0000 0.0163 -10.000 -0.5874 0.05151 0.04915 -0.0520 1.0000 0.0162 -9.750 -0.6140 0.04725 0.04478 -0.0511 1.0000 0.0160 -9.500 -0.6353 0.04425 0.04167 -0.0487 1.0000 0.0161 -9.250 -0.6563 0.04161 0.03893 -0.0446 1.0000 0.0161 -7.000 -0.7063 0.02580 0.02043 -0.0088 0.9909 0.0138 -6.750 -0.6787 0.02188 0.01622 -0.0090 0.9880 0.0124 -6.500 -0.6468 0.01958 0.01365 -0.0100 0.9854 0.0126 -6.250 -0.6125 0.01810 0.01201 -0.0115 0.9833 0.0131 -6.000 -0.5829 0.01658 0.01034 -0.0121 0.9792 0.0137 -5.750 -0.5570 0.01464 0.00827 -0.0122 0.9742 0.0150 -5.500 -0.5237 0.01376 0.00737 -0.0139 0.9710 0.0172 -5.250 -0.4918 0.01291 0.00643 -0.0151 0.9670 0.0190 -5.000 -0.4610 0.01227 0.00571 -0.0159 0.9609 0.0205 -4.750 -0.4291 0.01137 0.00473 -0.0171 0.9561 0.0265 -4.500 -0.4025 0.01066 0.00407 -0.0170 0.9472 0.0501 -4.250 -0.3785 0.00962 0.00350 -0.0169 0.9384 0.1591 -4.000 -0.3672 0.00806 0.00288 -0.0145 0.9257 0.3866 -3.750 -0.3500 0.00738 0.00264 -0.0125 0.9135 0.5074 -3.500 -0.3289 0.00712 0.00253 -0.0110 0.9006 0.5658 -3.250 -0.3069 0.00700 0.00245 -0.0097 0.8874 0.6112 -3.000 -0.2833 0.00692 0.00236 -0.0087 0.8740 0.6388 -2.750 -0.2580 0.00685 0.00224 -0.0081 0.8602 0.6535 -2.500 -0.2331 0.00678 0.00213 -0.0074 0.8460 0.6696 -2.250 -0.2086 0.00673 0.00202 -0.0066 0.8316 0.6876 -2.000 -0.1837 0.00668 0.00193 -0.0060 0.8173 0.7030 -1.750 -0.1582 0.00663 0.00185 -0.0055 0.8033 0.7146 -1.500 -0.1327 0.00660 0.00179 -0.0050 0.7898 0.7264 -1.250 -0.1070 0.00658 0.00173 -0.0045 0.7773 0.7376 -1.000 -0.0810 0.00658 0.00169 -0.0042 0.7656 0.7481 -0.750 -0.0550 0.00658 0.00166 -0.0038 0.7548 0.7592 -0.500 -0.0289 0.00659 0.00165 -0.0035 0.7449 0.7703 -0.250 -0.0029 0.00660 0.00165 -0.0032 0.7351 0.7822 0.000 0.0233 0.00661 0.00167 -0.0029 0.7263 0.7947 0.250 0.0494 0.00664 0.00169 -0.0026 0.7183 0.8079 0.500 0.0755 0.00665 0.00173 -0.0022 0.7097 0.8215 0.750 0.1019 0.00669 0.00177 -0.0020 0.7025 0.8350 1.000 0.1284 0.00671 0.00183 -0.0017 0.6949 0.8485 1.250 0.1552 0.00676 0.00189 -0.0015 0.6883 0.8615 1.500 0.1821 0.00679 0.00197 -0.0013 0.6811 0.8743 1.750 0.2094 0.00686 0.00205 -0.0012 0.6751 0.8867 2.000 0.2371 0.00690 0.00215 -0.0012 0.6674 0.8983 2.250 0.2667 0.00697 0.00225 -0.0016 0.6587 0.9083 2.500 0.2958 0.00705 0.00234 -0.0019 0.6467 0.9180 2.750 0.3239 0.00712 0.00244 -0.0019 0.6353 0.9283 3.000 0.3575 0.00722 0.00258 -0.0032 0.6232 0.9348 3.250 0.3875 0.00731 0.00270 -0.0037 0.6103 0.9429 3.500 0.4220 0.00744 0.00284 -0.0052 0.5887 0.9477 3.750 0.4494 0.00758 0.00294 -0.0051 0.5601 0.9556 4.000 0.4855 0.00783 0.00309 -0.0071 0.5121 0.9583 4.250 0.5130 0.00867 0.00337 -0.0076 0.3716 0.9627 4.500 0.5237 0.01101 0.00438 -0.0058 0.0825 0.9710 4.750 0.5540 0.01207 0.00517 -0.0069 0.0228 0.9747 5.000 0.5855 0.01263 0.00582 -0.0079 0.0197 0.9793 5.250 0.6143 0.01341 0.00666 -0.0086 0.0167 0.9839 5.500 0.6441 0.01456 0.00793 -0.0096 0.0148 0.9873 5.750 0.6746 0.01542 0.00891 -0.0106 0.0140 0.9913 6.000 0.7035 0.01656 0.01013 -0.0113 0.0135 0.9949 6.250 0.7341 0.01796 0.01163 -0.0123 0.0130 0.9975 6.500 0.7643 0.01982 0.01364 -0.0129 0.0133 0.9994 6.750 0.7855 0.02134 0.01530 -0.0117 0.0130 1.0000 7.000 0.7996 0.02265 0.01675 -0.0092 0.0127 1.0000 7.250 0.8132 0.02425 0.01853 -0.0066 0.0126 1.0000 13.000 0.6101 0.12482 0.12247 0.0129 0.0152 1.0000 13.250 0.6097 0.13018 0.12781 0.0106 0.0151 1.0000