XFOIL Version 6.94 Calculated polar for: NASA/LANGLEY MS(1)-0313 AIRFOIL 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 0.3659 0.01125 0.00620 -0.0773 0.8195 0.7751 0.500 0.4198 0.01097 0.00590 -0.0761 0.8026 0.7821 1.000 0.4755 0.01077 0.00567 -0.0755 0.7799 0.7892 1.500 0.5337 0.01065 0.00548 -0.0756 0.7549 0.7975 2.000 0.5898 0.01048 0.00526 -0.0752 0.7234 0.8042 2.500 0.6430 0.01046 0.00516 -0.0742 0.6684 0.8108 3.000 0.6876 0.01137 0.00526 -0.0717 0.4936 0.8192 3.500 0.7283 0.01315 0.00603 -0.0699 0.3061 0.8264 4.000 0.7712 0.01431 0.00670 -0.0679 0.2131 0.8335 4.500 0.8178 0.01531 0.00745 -0.0666 0.1726 0.8421 5.000 0.8671 0.01635 0.00838 -0.0660 0.1496 0.8496 5.500 0.9152 0.01683 0.00895 -0.0647 0.1382 0.8578 6.000 0.9568 0.01830 0.01036 -0.0624 0.1246 0.8673 6.500 1.0073 0.01910 0.01126 -0.0619 0.1213 0.8758 7.000 1.0517 0.01998 0.01230 -0.0599 0.1179 0.8857 7.500 1.0983 0.02107 0.01360 -0.0585 0.1148 0.8974 8.000 1.1412 0.02200 0.01467 -0.0565 0.1110 0.9096 8.500 1.1843 0.02314 0.01590 -0.0547 0.1069 0.9240 9.000 1.2240 0.02602 0.01895 -0.0525 0.0996 0.9435 9.500 1.2662 0.02642 0.01956 -0.0508 0.0977 1.0000 10.000 1.3168 0.02779 0.02111 -0.0513 0.0944 1.0000 10.500 1.3612 0.02937 0.02288 -0.0507 0.0901 1.0000 11.000 1.3973 0.03085 0.02460 -0.0487 0.0858 1.0000 11.500 1.4253 0.03240 0.02624 -0.0456 0.0816 1.0000 12.000 1.4438 0.03750 0.03169 -0.0425 0.0744 1.0000 12.500 1.4667 0.03813 0.03245 -0.0390 0.0727 1.0000 13.000 1.4852 0.03991 0.03446 -0.0358 0.0697 1.0000 13.500 1.5014 0.04200 0.03678 -0.0330 0.0651 1.0000 14.000 1.5203 0.04369 0.03854 -0.0310 0.0600 1.0000 14.500 1.5324 0.04650 0.04135 -0.0293 0.0551 1.0000 15.000 1.5027 0.05497 0.05024 -0.0263 0.0496 1.0000 15.500 1.5176 0.05834 0.05379 -0.0263 0.0478 1.0000 16.000 1.5191 0.06382 0.05950 -0.0266 0.0455 1.0000 16.500 1.5202 0.06982 0.06567 -0.0279 0.0432 1.0000 17.000 1.5144 0.07742 0.07341 -0.0306 0.0412 1.0000 17.500 1.4892 0.08871 0.08495 -0.0353 0.0397 1.0000 18.000 1.4443 0.10409 0.10062 -0.0427 0.0384 1.0000 18.500 1.3778 0.12478 0.12167 -0.0542 0.0377 1.0000