XFOIL Version 6.94 Calculated polar for: NACA 2414 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 0.2373 0.00730 0.00241 -0.0500 0.6944 0.7706 0.500 0.2884 0.00731 0.00250 -0.0482 0.6639 0.8379 1.000 0.3396 0.00744 0.00265 -0.0464 0.6334 0.8948 1.500 0.3956 0.00770 0.00283 -0.0456 0.6042 0.9375 2.000 0.4609 0.00801 0.00302 -0.0471 0.5749 0.9656 2.500 0.5385 0.00837 0.00323 -0.0515 0.5460 0.9811 3.000 0.6196 0.00868 0.00343 -0.0568 0.5158 0.9925 3.500 0.6994 0.00900 0.00360 -0.0620 0.4862 1.0000 4.000 0.7434 0.00921 0.00375 -0.0598 0.4601 1.0000 4.500 0.7866 0.00951 0.00394 -0.0573 0.4320 1.0000 5.000 0.8300 0.00986 0.00420 -0.0548 0.4028 1.0000 5.500 0.8723 0.01030 0.00450 -0.0521 0.3690 1.0000 6.000 0.9149 0.01080 0.00488 -0.0494 0.3327 1.0000 6.500 0.9566 0.01144 0.00535 -0.0468 0.2930 1.0000 7.000 0.9985 0.01218 0.00592 -0.0443 0.2508 1.0000 7.500 1.0397 0.01305 0.00661 -0.0418 0.2095 1.0000 8.000 1.0793 0.01404 0.00741 -0.0391 0.1705 1.0000 8.500 1.1175 0.01512 0.00832 -0.0363 0.1376 1.0000 9.000 1.1541 0.01624 0.00934 -0.0333 0.1117 1.0000 9.500 1.1853 0.01749 0.01049 -0.0295 0.0927 1.0000 10.000 1.2131 0.01882 0.01178 -0.0253 0.0791 1.0000 10.500 1.2400 0.02030 0.01327 -0.0213 0.0691 1.0000 11.000 1.2681 0.02180 0.01484 -0.0179 0.0620 1.0000 11.500 1.2913 0.02370 0.01683 -0.0143 0.0560 1.0000 12.000 1.3063 0.02630 0.01945 -0.0106 0.0510 1.0000 12.500 1.3296 0.02851 0.02182 -0.0081 0.0474 1.0000 13.000 1.3384 0.03205 0.02543 -0.0053 0.0442 1.0000 13.500 1.3536 0.03537 0.02893 -0.0034 0.0416 1.0000 14.000 1.3644 0.03929 0.03298 -0.0022 0.0392 1.0000 14.500 1.3622 0.04474 0.03856 -0.0011 0.0372 1.0000 15.000 1.3696 0.04956 0.04359 -0.0009 0.0355 1.0000 15.500 1.3718 0.05521 0.04940 -0.0012 0.0339 1.0000 16.000 1.3673 0.06178 0.05609 -0.0020 0.0326 1.0000 16.500 1.3606 0.06876 0.06323 -0.0029 0.0315 1.0000 17.000 1.3569 0.07585 0.07056 -0.0046 0.0305 1.0000 17.500 1.3514 0.08337 0.07827 -0.0067 0.0294 1.0000 18.000 1.3444 0.09128 0.08634 -0.0093 0.0285 1.0000 18.500 1.3367 0.09916 0.09431 -0.0118 0.0276 1.0000 19.000 1.3266 0.10744 0.10278 -0.0145 0.0268 1.0000 19.500 1.3134 0.11700 0.11260 -0.0187 0.0262 1.0000 20.000 1.2984 0.12706 0.12291 -0.0236 0.0256 1.0000 20.500 1.2827 0.13759 0.13368 -0.0292 0.0250 1.0000 21.000 1.2655 0.14870 0.14501 -0.0355 0.0245 1.0000 21.500 1.2482 0.16019 0.15671 -0.0426 0.0240 1.0000 22.000 1.2270 0.17310 0.16983 -0.0510 0.0236 1.0000