XFOIL Version 6.94 Calculated polar for: NACA 2.5411 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 0.3318 0.00758 0.00297 -0.0722 0.7981 0.9909 0.500 0.3987 0.00764 0.00280 -0.0744 0.7639 1.0000 1.000 0.4479 0.00779 0.00272 -0.0728 0.7289 1.0000 1.500 0.4973 0.00800 0.00272 -0.0713 0.6940 1.0000 2.000 0.5467 0.00826 0.00281 -0.0697 0.6597 1.0000 2.500 0.5964 0.00857 0.00294 -0.0683 0.6273 1.0000 3.000 0.6466 0.00890 0.00315 -0.0669 0.5965 1.0000 3.500 0.6971 0.00926 0.00338 -0.0657 0.5664 1.0000 4.000 0.7477 0.00964 0.00367 -0.0645 0.5356 1.0000 4.500 0.7978 0.01004 0.00398 -0.0632 0.5027 1.0000 5.000 0.8475 0.01049 0.00434 -0.0619 0.4683 1.0000 5.500 0.8970 0.01093 0.00474 -0.0606 0.4300 1.0000 6.000 0.9451 0.01148 0.00520 -0.0591 0.3841 1.0000 6.500 0.9905 0.01225 0.00578 -0.0573 0.3224 1.0000 7.000 1.0317 0.01344 0.00663 -0.0549 0.2418 1.0000 7.500 1.0681 0.01513 0.00784 -0.0522 0.1534 1.0000 8.000 1.1024 0.01700 0.00935 -0.0491 0.0959 1.0000 8.500 1.1358 0.01881 0.01100 -0.0458 0.0711 1.0000 9.000 1.1678 0.02054 0.01274 -0.0423 0.0579 1.0000 9.500 1.1952 0.02235 0.01461 -0.0382 0.0498 1.0000 10.000 1.2160 0.02443 0.01675 -0.0333 0.0445 1.0000 10.500 1.2379 0.02657 0.01898 -0.0292 0.0400 1.0000 11.000 1.2588 0.02898 0.02157 -0.0253 0.0364 1.0000 11.500 1.2762 0.03203 0.02465 -0.0216 0.0339 1.0000 12.000 1.2961 0.03487 0.02777 -0.0185 0.0315 1.0000 12.500 1.3148 0.03817 0.03108 -0.0158 0.0294 1.0000 13.500 1.3383 0.04600 0.03956 -0.0111 0.0263 1.0000 14.000 1.3493 0.05032 0.04402 -0.0093 0.0252 1.0000 14.500 1.3496 0.05632 0.05036 -0.0077 0.0244 1.0000 15.000 1.3342 0.06381 0.05835 -0.0077 0.0239 1.0000 15.500 1.3110 0.07293 0.06794 -0.0094 0.0234 1.0000 16.000 1.2804 0.08400 0.07945 -0.0131 0.0231 1.0000 16.500 1.2423 0.09751 0.09340 -0.0195 0.0229 1.0000 17.000 1.1924 0.11492 0.11126 -0.0293 0.0231 1.0000 17.500 1.1271 0.13831 0.13507 -0.0441 0.0237 1.0000