XFOIL Version 6.94 Calculated polar for: Eif385mod4 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.035 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- -3.000 0.0822 0.03281 0.02393 -0.0322 0.4989 0.6151 -2.750 0.1049 0.03353 0.02341 -0.0312 0.4144 0.6258 -2.500 0.1348 0.03355 0.02300 -0.0319 0.3925 0.6340 -2.250 0.1674 0.03361 0.02268 -0.0331 0.3788 0.6396 -2.000 0.2028 0.03362 0.02244 -0.0348 0.3673 0.6447 -1.750 0.2386 0.03385 0.02239 -0.0364 0.3571 0.6528 -1.500 0.2754 0.03390 0.02240 -0.0380 0.3493 0.6613 -1.250 0.3142 0.03408 0.02255 -0.0401 0.3425 0.6637 -1.000 0.3539 0.03444 0.02285 -0.0423 0.3380 0.6623 -0.750 0.3932 0.03494 0.02331 -0.0443 0.3348 0.6607 -0.500 0.4320 0.03555 0.02394 -0.0462 0.3323 0.6656 -0.250 0.4812 0.03577 0.02460 -0.0497 0.3303 1.0007 0.000 0.5177 0.03697 0.02562 -0.0513 0.3292 1.0007 0.250 0.5523 0.03822 0.02677 -0.0525 0.3286 1.0007 0.500 0.5852 0.03951 0.02802 -0.0535 0.3285 1.0007 0.750 0.6171 0.04082 0.02934 -0.0542 0.3289 1.0007 1.000 0.6480 0.04215 0.03073 -0.0549 0.3299 1.0007 1.250 0.6780 0.04360 0.03227 -0.0556 0.3309 1.0007 1.500 0.7069 0.04521 0.03399 -0.0561 0.3316 1.0007 1.750 0.7346 0.04695 0.03585 -0.0566 0.3320 1.0007 2.000 0.7609 0.04883 0.03788 -0.0570 0.3325 1.0007 2.250 0.7857 0.05087 0.04011 -0.0573 0.3337 1.0007 2.500 0.8083 0.05322 0.04276 -0.0577 0.3367 1.0007 2.750 0.8288 0.05603 0.04585 -0.0582 0.3419 1.0007 3.000 0.8485 0.05909 0.04908 -0.0586 0.3470 1.0007 3.250 0.8685 0.06235 0.05243 -0.0590 0.3517 1.0007 3.500 0.8922 0.06579 0.05584 -0.0596 0.3557 1.0007 3.750 0.8664 0.07247 0.06344 -0.0602 0.3769 1.0007 4.000 0.8967 0.07612 0.06695 -0.0614 0.3830 1.0007 5.000 0.4964 0.12570 0.11775 -0.0765 0.7527 1.0007