XFOIL Version 6.94 Calculated polar for: S4233-136-84 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.080 Re = 0.450 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- 0.000 0.3623 0.00798 0.00262 -0.0741 0.6616 0.7398 0.500 0.4179 0.00801 0.00264 -0.0740 0.6502 0.7697 1.000 0.4727 0.00800 0.00268 -0.0736 0.6381 0.8010 1.500 0.5266 0.00801 0.00277 -0.0731 0.6258 0.8351 2.000 0.5788 0.00803 0.00286 -0.0721 0.6136 0.8744 2.500 0.6293 0.00805 0.00294 -0.0707 0.6007 0.9242 3.000 0.6995 0.00809 0.00303 -0.0737 0.5863 0.9758 3.500 0.7694 0.00824 0.00316 -0.0771 0.5714 1.0000 4.000 0.8215 0.00846 0.00334 -0.0767 0.5563 1.0000 4.500 0.8744 0.00870 0.00356 -0.0764 0.5402 1.0000 5.000 0.9270 0.00897 0.00383 -0.0761 0.5226 1.0000 5.500 0.9791 0.00927 0.00412 -0.0756 0.5031 1.0000 6.000 1.0298 0.00964 0.00447 -0.0750 0.4811 1.0000 6.500 1.0793 0.01004 0.00487 -0.0741 0.4546 1.0000 7.000 1.1256 0.01058 0.00536 -0.0727 0.4206 1.0000 7.500 1.1674 0.01132 0.00597 -0.0707 0.3782 1.0000 8.000 1.2052 0.01224 0.00675 -0.0681 0.3300 1.0000 8.500 1.2353 0.01344 0.00774 -0.0644 0.2769 1.0000 9.000 1.2514 0.01495 0.00898 -0.0585 0.2196 1.0000 9.500 1.2581 0.01704 0.01076 -0.0520 0.1598 1.0000 10.000 1.2631 0.01961 0.01306 -0.0463 0.1057 1.0000 10.500 1.2632 0.02287 0.01603 -0.0411 0.0590 1.0000 11.000 1.2583 0.02692 0.01987 -0.0364 0.0246 1.0000 11.500 1.2640 0.03062 0.02363 -0.0332 0.0178 1.0000 12.000 1.2741 0.03421 0.02740 -0.0309 0.0156 1.0000 12.500 1.2797 0.03843 0.03178 -0.0291 0.0143 1.0000 13.000 1.2761 0.04391 0.03744 -0.0275 0.0135 1.0000 13.500 1.2746 0.04957 0.04329 -0.0267 0.0131 1.0000 14.000 1.2748 0.05542 0.04935 -0.0265 0.0126 1.0000 14.500 1.2745 0.06162 0.05576 -0.0267 0.0123 1.0000 15.000 1.2773 0.06776 0.06207 -0.0274 0.0115 1.0000 15.500 1.2772 0.07445 0.06893 -0.0285 0.0111 1.0000 16.000 1.2774 0.08131 0.07597 -0.0298 0.0108 1.0000 16.500 1.2781 0.08823 0.08306 -0.0312 0.0105 1.0000 17.000 1.2795 0.09510 0.09010 -0.0326 0.0103 1.0000 17.500 1.2810 0.10215 0.09737 -0.0344 0.0101 1.0000 18.000 1.2766 0.11030 0.10583 -0.0365 0.0100 1.0000 18.500 1.2676 0.11985 0.11569 -0.0404 0.0099 1.0000 19.000 1.2514 0.13126 0.12743 -0.0462 0.0099 1.0000 19.500 1.2320 0.14372 0.14021 -0.0532 0.0099 1.0000 20.000 1.2128 0.15679 0.15358 -0.0612 0.0099 1.0000 20.500 1.1907 0.17141 0.16850 -0.0708 0.0100 1.0000 21.000 1.1686 0.18719 0.18456 -0.0814 0.0101 1.0000