XFOIL Version 6.94 Calculated polar for: MRC-16 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.080 Re = 0.300 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- 0.000 0.3431 0.00945 0.00428 -0.0638 0.7287 0.9476 0.500 0.4227 0.00962 0.00426 -0.0686 0.7112 0.9636 1.000 0.5025 0.00974 0.00423 -0.0737 0.6925 0.9778 1.500 0.5876 0.00978 0.00413 -0.0802 0.6728 0.9884 2.000 0.6706 0.00979 0.00405 -0.0864 0.6518 0.9989 2.500 0.7208 0.00987 0.00404 -0.0860 0.6311 1.0000 3.000 0.7656 0.01000 0.00410 -0.0842 0.6102 1.0000 3.500 0.8090 0.01019 0.00424 -0.0822 0.5891 1.0000 4.000 0.8514 0.01043 0.00442 -0.0798 0.5677 1.0000 4.500 0.8928 0.01071 0.00464 -0.0772 0.5459 1.0000 5.000 0.9335 0.01104 0.00494 -0.0744 0.5237 1.0000 5.500 0.9735 0.01143 0.00526 -0.0715 0.5010 1.0000 6.000 1.0129 0.01184 0.00564 -0.0685 0.4774 1.0000 6.500 1.0517 0.01228 0.00608 -0.0654 0.4524 1.0000 7.000 1.0902 0.01281 0.00659 -0.0623 0.4263 1.0000 7.500 1.1283 0.01341 0.00717 -0.0593 0.3993 1.0000 8.000 1.1647 0.01409 0.00782 -0.0561 0.3699 1.0000 8.500 1.1987 0.01488 0.00861 -0.0526 0.3397 1.0000 9.000 1.2260 0.01585 0.00949 -0.0481 0.3084 1.0000 9.500 1.2528 0.01695 0.01057 -0.0438 0.2752 1.0000 10.000 1.2772 0.01834 0.01190 -0.0397 0.2417 1.0000 10.500 1.2984 0.02006 0.01359 -0.0356 0.2087 1.0000 11.000 1.3159 0.02219 0.01563 -0.0316 0.1760 1.0000 11.500 1.3302 0.02474 0.01810 -0.0279 0.1432 1.0000 12.000 1.3418 0.02771 0.02102 -0.0245 0.1132 1.0000 12.500 1.3472 0.03139 0.02464 -0.0212 0.0862 1.0000 13.000 1.3466 0.03588 0.02907 -0.0183 0.0642 1.0000 13.500 1.3419 0.04106 0.03431 -0.0159 0.0493 1.0000 14.000 1.3381 0.04661 0.04002 -0.0143 0.0404 1.0000 14.500 1.3176 0.05436 0.04789 -0.0132 0.0340 1.0000 15.000 1.3176 0.06027 0.05405 -0.0130 0.0306 1.0000 15.500 1.3092 0.06740 0.06136 -0.0134 0.0275 1.0000 16.000 1.2899 0.07611 0.07023 -0.0142 0.0249 1.0000 16.500 1.2792 0.08380 0.07814 -0.0149 0.0231 1.0000 17.000 1.2750 0.09119 0.08577 -0.0165 0.0215 1.0000 17.500 1.2680 0.09911 0.09390 -0.0186 0.0200 1.0000 18.000 1.2592 0.10734 0.10233 -0.0209 0.0189 1.0000 18.500 1.2498 0.11587 0.11105 -0.0238 0.0180 1.0000 19.000 1.2388 0.12466 0.12006 -0.0268 0.0171 1.0000 19.500 1.2214 0.13455 0.13022 -0.0305 0.0164 1.0000 20.500 1.1663 0.16132 0.15769 -0.0444 0.0158 1.0000 21.000 1.1338 0.17789 0.17459 -0.0547 0.0158 1.0000