XFOIL Version 6.94 Calculated polar for: NACA 66(3)-418 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 -0.0708 0.02215 0.01788 -0.0035 0.7246 0.7707 0.500 -0.0184 0.02224 0.01794 -0.0032 0.7205 0.7760 1.000 0.0448 0.02170 0.01734 -0.0052 0.7172 0.7777 1.500 0.1061 0.02134 0.01695 -0.0070 0.7145 0.7797 2.000 0.1685 0.02106 0.01667 -0.0088 0.7122 0.7827 2.500 0.2394 0.02046 0.01608 -0.0119 0.7102 0.7850 3.000 0.3112 0.01984 0.01544 -0.0151 0.7083 0.7872 3.500 0.3861 0.01925 0.01486 -0.0189 0.7052 0.7893 4.000 0.3378 0.02161 0.01724 -0.0033 0.6834 0.7939 4.500 0.3888 0.02129 0.01696 -0.0031 0.6754 0.7956 5.000 0.5305 0.01701 0.01271 -0.0153 0.6756 0.7959 5.500 0.7419 0.01192 0.00747 -0.0409 0.6561 0.7952 6.000 0.7246 0.01275 0.00840 -0.0283 0.6342 0.7974 6.500 0.7429 0.01267 0.00794 -0.0218 0.5544 0.8006 7.000 0.7159 0.01409 0.00903 -0.0090 0.4821 0.8092 7.500 0.6824 0.01622 0.01084 0.0042 0.4081 0.8168 8.000 0.6570 0.01865 0.01301 0.0152 0.3183 0.8237 8.500 0.6382 0.02125 0.01528 0.0244 0.2385 0.8307 9.000 0.6302 0.02367 0.01717 0.0316 0.1334 0.8375 9.500 0.6192 0.02644 0.01932 0.0386 0.0384 0.8434 10.500 0.6475 0.03044 0.02363 0.0464 0.0194 0.8573 11.000 0.6640 0.03227 0.02568 0.0500 0.0186 0.8705 11.500 0.6783 0.03425 0.02789 0.0539 0.0182 0.8823 12.000 0.6958 0.03627 0.03011 0.0571 0.0179 0.8934 12.500 0.7211 0.03817 0.03229 0.0595 0.0179 0.9068 13.000 0.7504 0.03989 0.03430 0.0619 0.0180 0.9312 14.000 0.8244 0.04693 0.04207 0.0608 0.0188 0.9840 14.500 0.8324 0.05249 0.04799 0.0615 0.0193 1.0000 15.000 0.8146 0.05927 0.05512 0.0634 0.0197 1.0000 15.500 0.7853 0.06728 0.06349 0.0646 0.0201 1.0000 16.000 0.7426 0.07717 0.07371 0.0641 0.0205 1.0000 16.500 0.6871 0.09007 0.08693 0.0610 0.0209 1.0000 18.000 0.5364 0.14734 0.14479 0.0357 0.0302 1.0000 18.500 0.5325 0.15661 0.15404 0.0316 0.0295 1.0000 19.000 0.5354 0.16409 0.16150 0.0282 0.0285 1.0000 19.500 0.5436 0.17013 0.16752 0.0254 0.0273 1.0000 20.000 0.5540 0.17518 0.17257 0.0228 0.0257 1.0000 20.500 0.5609 0.18128 0.17865 0.0200 0.0242 1.0000