XFOIL Version 6.94 Calculated polar for: Profil 387 Dicke 9.06% 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 0.4006 0.00807 0.00264 -0.0814 0.6812 1.0000 0.500 0.4555 0.00825 0.00265 -0.0811 0.6684 1.0000 1.000 0.5104 0.00847 0.00274 -0.0809 0.6561 1.0000 1.500 0.5655 0.00872 0.00286 -0.0807 0.6448 1.0000 2.000 0.6206 0.00896 0.00301 -0.0805 0.6329 1.0000 2.500 0.6755 0.00919 0.00322 -0.0803 0.6201 1.0000 3.000 0.7302 0.00943 0.00344 -0.0800 0.6065 1.0000 3.500 0.7846 0.00964 0.00366 -0.0797 0.5915 1.0000 4.000 0.8388 0.00985 0.00389 -0.0793 0.5756 1.0000 4.500 0.8925 0.01004 0.00415 -0.0788 0.5578 1.0000 5.000 0.9455 0.01020 0.00437 -0.0781 0.5361 1.0000 5.500 0.9968 0.01035 0.00456 -0.0771 0.5017 1.0000 6.000 1.0467 0.01066 0.00487 -0.0760 0.4548 1.0000 6.500 1.0900 0.01158 0.00547 -0.0740 0.3549 1.0000 7.000 1.1208 0.01395 0.00699 -0.0709 0.1959 1.0000 7.500 1.1436 0.01710 0.00921 -0.0669 0.0497 1.0000 8.000 1.1727 0.01944 0.01154 -0.0631 0.0236 1.0000 8.500 1.2008 0.02150 0.01376 -0.0594 0.0200 1.0000 9.500 1.2254 0.02677 0.01944 -0.0484 0.0177 1.0000 10.000 1.2385 0.02998 0.02288 -0.0442 0.0171 1.0000 10.500 1.2567 0.03355 0.02668 -0.0408 0.0166 1.0000 11.000 1.2818 0.03762 0.03105 -0.0379 0.0164 1.0000 11.500 1.3076 0.04285 0.03673 -0.0353 0.0167 1.0000 12.000 1.3161 0.04968 0.04413 -0.0326 0.0173 1.0000 12.500 1.3058 0.05690 0.05187 -0.0305 0.0174 1.0000 13.000 1.2849 0.06509 0.06054 -0.0299 0.0174 1.0000 13.500 1.2540 0.07536 0.07125 -0.0316 0.0176 1.0000 14.000 1.2167 0.08767 0.08396 -0.0357 0.0181 1.0000 14.500 1.1754 0.10213 0.09877 -0.0426 0.0184 1.0000 15.000 1.1602 0.11364 0.11056 -0.0485 0.0197 1.0000