XFOIL Version 6.96 Calculated polar for: NACA 66 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -15.000 -0.9678 0.05190 0.04975 -0.0652 1.0000 0.0064 -14.500 -1.0109 0.04067 0.03801 -0.0695 0.9556 0.0064 -14.250 -0.9977 0.03999 0.03726 -0.0692 0.9319 0.0066 -14.000 -1.0180 0.03651 0.03349 -0.0670 0.9124 0.0066 -13.750 -1.0277 0.03407 0.03081 -0.0647 0.8994 0.0066 -13.500 -1.0226 0.03293 0.02957 -0.0631 0.8896 0.0067 -13.250 -1.0268 0.03095 0.02738 -0.0605 0.8804 0.0068 -13.000 -1.0217 0.02981 0.02610 -0.0585 0.8728 0.0069 -12.750 -1.0185 0.02842 0.02456 -0.0561 0.8655 0.0069 -12.250 -1.0063 0.02613 0.02196 -0.0513 0.8532 0.0072 -12.000 -0.9995 0.02496 0.02062 -0.0487 0.8474 0.0072 -11.750 -0.9899 0.02379 0.01927 -0.0466 0.8427 0.0073 -11.500 -0.9753 0.02280 0.01815 -0.0451 0.8382 0.0075 -11.250 -0.9595 0.02186 0.01705 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0.0067 0.00576 0.00106 -0.0305 0.7436 0.5688 -1.000 0.0300 0.00533 0.00107 -0.0298 0.7421 0.7007 -0.750 0.0576 0.00528 0.00109 -0.0298 0.7408 0.7295 -0.500 0.0859 0.00526 0.00112 -0.0300 0.7398 0.7473 -0.250 0.1143 0.00525 0.00115 -0.0302 0.7386 0.7616 0.000 0.1427 0.00525 0.00119 -0.0304 0.7374 0.7733 0.250 0.1716 0.00526 0.00120 -0.0308 0.7356 0.7788 0.500 0.2006 0.00527 0.00120 -0.0311 0.7327 0.7817 0.750 0.2292 0.00527 0.00120 -0.0314 0.7291 0.7839 1.000 0.2579 0.00528 0.00120 -0.0317 0.7253 0.7860 1.250 0.2867 0.00527 0.00122 -0.0321 0.7212 0.7883 1.500 0.3152 0.00527 0.00121 -0.0323 0.7141 0.7907 1.750 0.3437 0.00527 0.00122 -0.0326 0.7050 0.7931 2.000 0.3719 0.00530 0.00122 -0.0328 0.6920 0.7957 2.250 0.3996 0.00532 0.00123 -0.0329 0.6725 0.7981 2.500 0.4225 0.00564 0.00126 -0.0320 0.5886 0.8008 2.750 0.4320 0.00702 0.00179 -0.0292 0.3882 0.8043 3.000 0.4466 0.00800 0.00219 -0.0273 0.2463 0.8079 3.250 0.4655 0.00866 0.00248 -0.0261 0.1579 0.8110 3.500 0.4859 0.00917 0.00275 -0.0250 0.0940 0.8140 3.750 0.5072 0.00960 0.00301 -0.0241 0.0490 0.8173 4.000 0.5313 0.00986 0.00321 -0.0236 0.0347 0.8206 4.250 0.5558 0.01008 0.00341 -0.0233 0.0284 0.8241 4.500 0.5806 0.01027 0.00361 -0.0229 0.0261 0.8275 4.750 0.6046 0.01049 0.00383 -0.0224 0.0237 0.8311 5.000 0.6282 0.01073 0.00409 -0.0219 0.0211 0.8350 5.250 0.6524 0.01093 0.00430 -0.0214 0.0203 0.8388 5.500 0.6761 0.01115 0.00455 -0.0209 0.0190 0.8424 5.750 0.6991 0.01139 0.00481 -0.0202 0.0179 0.8464 6.000 0.7212 0.01167 0.00510 -0.0194 0.0166 0.8508 6.250 0.7429 0.01199 0.00545 -0.0186 0.0157 0.8553 6.500 0.7649 0.01224 0.00574 -0.0177 0.0153 0.8596 6.750 0.7859 0.01253 0.00608 -0.0167 0.0147 0.8646 7.000 0.8061 0.01280 0.00638 -0.0156 0.0141 0.8700 7.250 0.8246 0.01308 0.00670 -0.0141 0.0135 0.8756 7.500 0.8431 0.01337 0.00702 -0.0127 0.0128 0.8823 7.750 0.8596 0.01380 0.00749 -0.0109 0.0121 0.8893 8.000 0.8761 0.01423 0.00798 -0.0092 0.0118 0.8973 8.250 0.8934 0.01462 0.00844 -0.0076 0.0116 0.9052 8.500 0.9106 0.01501 0.00890 -0.0061 0.0113 0.9144 8.750 0.9270 0.01542 0.00940 -0.0044 0.0111 0.9248 9.000 0.9427 0.01589 0.00994 -0.0026 0.0109 0.9375 9.250 0.9597 0.01637 0.01051 -0.0012 0.0106 0.9540 9.500 0.9844 0.01689 0.01109 -0.0015 0.0103 0.9722 9.750 1.0116 0.01747 0.01173 -0.0025 0.0099 1.0000 10.000 1.0295 0.01800 0.01229 -0.0014 0.0097 1.0000 10.250 1.0469 0.01857 0.01290 -0.0003 0.0095 1.0000 10.500 1.0637 0.01919 0.01354 0.0008 0.0092 1.0000 10.750 1.0785 0.01998 0.01439 0.0021 0.0090 1.0000 11.000 1.0912 0.02098 0.01546 0.0037 0.0087 1.0000 11.250 1.1072 0.02166 0.01621 0.0048 0.0086 1.0000 11.500 1.1225 0.02244 0.01706 0.0060 0.0085 1.0000 11.750 1.1366 0.02331 0.01802 0.0073 0.0084 1.0000 12.000 1.1513 0.02413 0.01892 0.0084 0.0082 1.0000 12.250 1.1644 0.02509 0.01996 0.0097 0.0081 1.0000 12.500 1.1779 0.02601 0.02097 0.0108 0.0080 1.0000 12.750 1.1896 0.02709 0.02215 0.0121 0.0078 1.0000 13.000 1.2013 0.02818 0.02333 0.0134 0.0077 1.0000 13.250 1.2111 0.02942 0.02467 0.0147 0.0076 1.0000 13.500 1.2216 0.03058 0.02592 0.0158 0.0074 1.0000 13.750 1.2311 0.03184 0.02729 0.0170 0.0073 1.0000 14.000 1.2392 0.03323 0.02877 0.0182 0.0072 1.0000 14.250 1.2485 0.03449 0.03011 0.0192 0.0071 1.0000 14.500 1.2566 0.03587 0.03157 0.0202 0.0069 1.0000 14.750 1.2645 0.03729 0.03306 0.0211 0.0068 1.0000 15.000 1.2707 0.03888 0.03474 0.0219 0.0067 1.0000 15.250 1.2726 0.04097 0.03695 0.0229 0.0067 1.0000 15.500 1.2776 0.04275 0.03880 0.0235 0.0066 1.0000 15.750 1.2772 0.04518 0.04135 0.0242 0.0065 1.0000 16.000 1.2712 0.04835 0.04466 0.0248 0.0064 1.0000 16.250 1.2651 0.05168 0.04814 0.0250 0.0063 1.0000 16.500 1.2550 0.05567 0.05229 0.0248 0.0063 1.0000 16.750 1.2410 0.06051 0.05730 0.0240 0.0062 1.0000 17.000 1.2317 0.06504 0.06199 0.0227 0.0062 1.0000 17.250 1.2203 0.07021 0.06732 0.0208 0.0061 1.0000 17.500 1.2002 0.07726 0.07455 0.0176 0.0061 1.0000 17.750 1.1836 0.08431 0.08176 0.0138 0.0061 1.0000 18.000 1.1589 0.09346 0.09109 0.0085 0.0061 1.0000 18.250 1.1151 0.10774 0.10560 -0.0002 0.0062 1.0000