XFOIL Version 6.94 Calculated polar for: MH 201 13.08% 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 0.4111 0.01108 0.00612 -0.0936 0.8059 0.7987 0.500 0.4684 0.01112 0.00605 -0.0933 0.7904 0.8097 1.000 0.5198 0.01115 0.00609 -0.0923 0.7757 0.8201 1.500 0.5766 0.01112 0.00600 -0.0923 0.7583 0.8269 2.000 0.6302 0.01088 0.00573 -0.0916 0.7391 0.8370 2.500 0.6775 0.01074 0.00564 -0.0895 0.7178 0.8461 3.000 0.7316 0.01072 0.00556 -0.0890 0.6932 0.8531 3.500 0.7825 0.01069 0.00549 -0.0878 0.6604 0.8616 4.000 0.8344 0.01078 0.00554 -0.0871 0.6227 0.8669 4.500 0.8832 0.01102 0.00559 -0.0858 0.5700 0.8719 5.000 0.9253 0.01135 0.00573 -0.0832 0.5151 0.8798 5.500 0.9620 0.01192 0.00609 -0.0796 0.4539 0.8896 6.000 1.0018 0.01260 0.00665 -0.0770 0.3993 0.8985 6.500 1.0406 0.01346 0.00729 -0.0744 0.3416 0.9059 7.000 1.0747 0.01427 0.00792 -0.0710 0.2917 0.9160 7.500 1.1048 0.01509 0.00864 -0.0667 0.2513 0.9290 8.000 1.1373 0.01608 0.00954 -0.0633 0.2139 0.9444 9.000 1.2097 0.01871 0.01201 -0.0593 0.1487 1.0000 9.500 1.2410 0.02074 0.01390 -0.0573 0.1215 1.0000 10.000 1.2807 0.02205 0.01546 -0.0562 0.1061 1.0000 10.500 1.3033 0.02448 0.01789 -0.0530 0.0898 1.0000 11.000 1.3346 0.02622 0.01979 -0.0510 0.0799 1.0000 11.500 1.3433 0.02985 0.02344 -0.0469 0.0656 1.0000 12.000 1.3732 0.03164 0.02544 -0.0454 0.0595 1.0000 12.500 1.3888 0.03465 0.02850 -0.0430 0.0510 1.0000 13.000 1.3889 0.03950 0.03357 -0.0396 0.0435 1.0000 13.500 1.4043 0.04301 0.03732 -0.0382 0.0394 1.0000 14.000 1.4106 0.04761 0.04212 -0.0368 0.0348 1.0000 14.500 1.4074 0.05351 0.04823 -0.0358 0.0315 1.0000 15.500 1.3721 0.07031 0.06589 -0.0356 0.0266 1.0000 16.000 1.3721 0.07732 0.07317 -0.0380 0.0250 1.0000 16.500 1.3631 0.08616 0.08229 -0.0416 0.0229 1.0000 17.000 1.3489 0.09624 0.09264 -0.0465 0.0208 1.0000 17.500 1.3296 0.10751 0.10418 -0.0525 0.0194 1.0000 18.000 1.3055 0.12002 0.11696 -0.0600 0.0184 1.0000 18.500 1.2761 0.13353 0.13076 -0.0689 0.0177 1.0000 19.000 1.2258 0.15314 0.15078 -0.0820 0.0181 1.0000