XFOIL Version 6.94 Calculated polar for: SD2030-086-88 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 0.3635 0.00871 0.00434 -0.0821 0.9171 0.9933 0.500 0.4397 0.00819 0.00377 -0.0861 0.9025 1.0000 1.000 0.4832 0.00788 0.00341 -0.0833 0.8805 1.0000 1.500 0.5292 0.00762 0.00309 -0.0808 0.8567 1.0000 2.000 0.5727 0.00751 0.00295 -0.0778 0.8282 1.0000 2.500 0.6165 0.00749 0.00287 -0.0749 0.7946 1.0000 3.000 0.6590 0.00757 0.00287 -0.0716 0.7491 1.0000 3.500 0.7000 0.00782 0.00291 -0.0681 0.6804 1.0000 4.000 0.7367 0.00847 0.00310 -0.0638 0.5725 1.0000 4.500 0.7704 0.00955 0.00361 -0.0594 0.4459 1.0000 5.000 0.8067 0.01073 0.00426 -0.0560 0.3309 1.0000 6.000 0.8875 0.01305 0.00588 -0.0510 0.1677 1.0000 6.500 0.9282 0.01434 0.00692 -0.0486 0.1157 1.0000 7.000 0.9675 0.01579 0.00823 -0.0460 0.0837 1.0000 7.500 1.0094 0.01698 0.00949 -0.0438 0.0654 1.0000 8.000 1.0501 0.01822 0.01084 -0.0415 0.0516 1.0000 8.500 1.0892 0.01957 0.01229 -0.0391 0.0398 1.0000 9.000 1.1249 0.02123 0.01398 -0.0361 0.0224 1.0000 9.500 1.1499 0.02389 0.01693 -0.0314 0.0171 1.0000 10.000 1.1708 0.02664 0.01988 -0.0264 0.0147 1.0000 10.500 1.1852 0.03161 0.02529 -0.0212 0.0137 1.0000 11.000 1.1975 0.03589 0.03009 -0.0162 0.0133 1.0000 11.500 1.1981 0.04052 0.03523 -0.0108 0.0127 1.0000 12.000 1.1889 0.04571 0.04090 -0.0061 0.0122 1.0000 12.500 1.1680 0.05244 0.04809 -0.0031 0.0118 1.0000 13.000 1.1385 0.06114 0.05724 -0.0033 0.0117 1.0000 13.500 1.0997 0.07320 0.06972 -0.0081 0.0117 1.0000 14.000 1.0498 0.09105 0.08797 -0.0194 0.0121 1.0000 14.500 0.9793 0.11898 0.11620 -0.0375 0.0134 1.0000 15.000 0.7102 0.14985 0.14750 -0.0563 0.0192 1.0000