XFOIL Version 6.94 Calculated polar for: Eif385mod2 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.030 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- -3.000 -0.0825 0.04171 0.03092 -0.0183 0.9993 0.3939 -2.750 0.0817 0.03624 0.02565 -0.0405 0.8908 0.4089 -2.500 0.1751 0.03464 0.02164 -0.0471 0.4698 0.4203 -2.250 0.2008 0.03506 0.02148 -0.0462 0.4321 0.4301 -2.000 0.2295 0.03542 0.02143 -0.0459 0.4115 0.4421 -1.750 0.2594 0.03560 0.02146 -0.0458 0.3971 0.4556 -1.500 0.2905 0.03564 0.02157 -0.0459 0.3881 0.4775 -1.250 0.3213 0.03548 0.02179 -0.0459 0.3814 0.5121 -0.750 0.4018 0.03523 0.02246 -0.0486 0.3706 1.0007 -0.500 0.4384 0.03630 0.02315 -0.0497 0.3676 1.0007 -0.250 0.4732 0.03727 0.02395 -0.0505 0.3655 1.0007 0.000 0.5071 0.03831 0.02488 -0.0513 0.3639 1.0007 0.250 0.5407 0.03946 0.02596 -0.0522 0.3624 1.0007 0.500 0.5727 0.04069 0.02717 -0.0529 0.3606 1.0007 0.750 0.6033 0.04203 0.02850 -0.0534 0.3587 1.0007 1.000 0.6328 0.04348 0.02995 -0.0539 0.3568 1.0007 1.250 0.6613 0.04506 0.03157 -0.0544 0.3554 1.0007 1.500 0.6890 0.04679 0.03336 -0.0548 0.3552 1.0007 1.750 0.7158 0.04872 0.03541 -0.0554 0.3568 1.0007 2.000 0.7416 0.05085 0.03766 -0.0560 0.3590 1.0007 2.250 0.7663 0.05319 0.04012 -0.0565 0.3616 1.0007 2.500 0.7902 0.05573 0.04272 -0.0571 0.3643 1.0007 2.750 0.8134 0.05849 0.04552 -0.0576 0.3671 1.0007 3.000 0.8254 0.06168 0.04921 -0.0582 0.3738 1.0007 3.250 0.8272 0.06644 0.05440 -0.0588 0.3835 1.0007 3.500 0.8394 0.07055 0.05857 -0.0594 0.3904 1.0007 3.750 0.7947 0.07945 0.06801 -0.0599 0.4103 1.0007 4.000 0.8213 0.08320 0.07170 -0.0614 0.4182 1.0007 4.750 0.2711 0.11561 0.10643 -0.0454 0.7639 1.0007 5.000 0.2858 0.11841 0.10910 -0.0460 0.7545 1.0007