XFOIL Version 6.96 Calculated polar for: NACA 64(3)-618 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 ------ -------- --------- --------- -------- -------- -------- -19.750 -1.0048 0.08347 0.08007 -0.0766 1.0000 0.0146 -19.500 -1.0176 0.07810 0.07460 -0.0795 1.0000 0.0146 -19.250 -1.0269 0.07327 0.06968 -0.0821 1.0000 0.0148 -19.000 -1.0348 0.06885 0.06516 -0.0843 1.0000 0.0149 -18.750 -1.0388 0.06507 0.06130 -0.0861 1.0000 0.0151 -18.500 -1.0417 0.06154 0.05769 -0.0878 1.0000 0.0152 -18.250 -1.0436 0.05822 0.05430 -0.0892 1.0000 0.0154 -18.000 -1.0455 0.05505 0.05104 -0.0905 1.0000 0.0155 -17.750 -1.0417 0.05260 0.04852 -0.0914 1.0000 0.0159 -17.500 -1.0418 0.04978 0.04563 -0.0924 1.0000 0.0159 -17.250 -1.0380 0.04748 0.04326 -0.0931 1.0000 0.0161 -17.000 -1.0339 0.04526 0.04097 -0.0936 1.0000 0.0162 -16.750 -1.0308 0.04304 0.03868 -0.0941 1.0000 0.0163 -16.500 -1.0293 0.04073 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-0.1104 0.5744 0.4807 -2.000 0.2739 0.00718 0.00169 -0.1108 0.5706 0.4942 -1.750 0.3033 0.00720 0.00171 -0.1111 0.5666 0.5087 -1.250 0.3619 0.00724 0.00173 -0.1119 0.5595 0.5197 -1.000 0.3914 0.00726 0.00174 -0.1122 0.5561 0.5233 -0.750 0.4208 0.00729 0.00175 -0.1126 0.5528 0.5264 -0.500 0.4500 0.00731 0.00176 -0.1129 0.5495 0.5295 -0.250 0.4790 0.00736 0.00179 -0.1132 0.5462 0.5322 0.000 0.5082 0.00739 0.00182 -0.1136 0.5436 0.5352 0.250 0.5377 0.00741 0.00185 -0.1140 0.5411 0.5383 0.500 0.5670 0.00745 0.00188 -0.1143 0.5383 0.5410 0.750 0.5961 0.00749 0.00192 -0.1146 0.5355 0.5433 1.000 0.6251 0.00753 0.00196 -0.1150 0.5328 0.5464 1.250 0.6539 0.00758 0.00202 -0.1153 0.5300 0.5496 1.500 0.6826 0.00765 0.00208 -0.1155 0.5273 0.5529 1.750 0.7118 0.00768 0.00213 -0.1159 0.5252 0.5563 2.000 0.7409 0.00772 0.00219 -0.1162 0.5222 0.5595 2.500 0.7982 0.00784 0.00233 -0.1167 0.5153 0.5662 2.750 0.8263 0.00792 0.00241 -0.1169 0.5118 0.5701 3.000 0.8549 0.00798 0.00249 -0.1172 0.5088 0.5741 3.250 0.8837 0.00803 0.00258 -0.1175 0.5063 0.5779 3.500 0.9122 0.00809 0.00266 -0.1177 0.5034 0.5817 3.750 0.9403 0.00816 0.00276 -0.1179 0.4991 0.5864 4.000 0.9673 0.00828 0.00287 -0.1179 0.4926 0.5914 4.250 0.9955 0.00835 0.00297 -0.1181 0.4864 0.5960 4.750 1.0493 0.00858 0.00320 -0.1180 0.4691 0.6048 5.000 1.0754 0.00873 0.00334 -0.1178 0.4606 0.6099 5.250 1.1026 0.00883 0.00347 -0.1179 0.4531 0.6150 5.500 1.1274 0.00904 0.00363 -0.1175 0.4373 0.6194 5.750 1.1485 0.00940 0.00388 -0.1165 0.4030 0.6247 6.000 1.1603 0.01022 0.00440 -0.1139 0.3473 0.6302 6.250 1.1734 0.01094 0.00492 -0.1116 0.3047 0.6355 6.500 1.1865 0.01160 0.00541 -0.1093 0.2694 0.6404 6.750 1.1958 0.01223 0.00591 -0.1062 0.2379 0.6463 7.000 1.2039 0.01286 0.00643 -0.1030 0.2115 0.6524 7.500 1.2194 0.01428 0.00765 -0.0968 0.1633 0.6641 7.750 1.2247 0.01514 0.00840 -0.0936 0.1399 0.6708 8.250 1.2374 0.01694 0.01007 -0.0880 0.1022 0.6845 8.500 1.2447 0.01790 0.01097 -0.0855 0.0881 0.6920 8.750 1.2528 0.01887 0.01192 -0.0833 0.0760 0.6989 9.000 1.2613 0.01988 0.01291 -0.0813 0.0658 0.7067 9.250 1.2710 0.02089 0.01391 -0.0795 0.0586 0.7138 9.500 1.2805 0.02194 0.01497 -0.0779 0.0520 0.7209 9.750 1.2899 0.02305 0.01609 -0.0763 0.0462 0.7288 10.000 1.2999 0.02418 0.01723 -0.0748 0.0413 0.7358 10.250 1.3101 0.02532 0.01840 -0.0735 0.0375 0.7438 10.500 1.3196 0.02655 0.01967 -0.0722 0.0342 0.7515 10.750 1.3297 0.02778 0.02094 -0.0710 0.0314 0.7596 11.000 1.3395 0.02907 0.02226 -0.0699 0.0291 0.7682 11.250 1.3492 0.03039 0.02363 -0.0688 0.0274 0.7773 11.500 1.3587 0.03176 0.02505 -0.0678 0.0256 0.7874 11.750 1.3684 0.03315 0.02651 -0.0669 0.0243 0.7986 12.000 1.3773 0.03465 0.02806 -0.0660 0.0230 0.8094 12.250 1.3868 0.03611 0.02959 -0.0651 0.0219 0.8225 12.500 1.3958 0.03765 0.03120 -0.0643 0.0209 0.8369 12.750 1.4042 0.03923 0.03287 -0.0635 0.0198 0.8534 13.250 1.4175 0.04234 0.03622 -0.0613 0.0182 0.9217 13.750 1.4333 0.04590 0.03991 -0.0602 0.0165 1.0000 14.000 1.4414 0.04783 0.04188 -0.0599 0.0157 1.0000 14.250 1.4499 0.04974 0.04382 -0.0596 0.0150 1.0000 14.500 1.4573 0.05179 0.04591 -0.0594 0.0143 1.0000 14.750 1.4645 0.05390 0.04805 -0.0592 0.0137 1.0000 15.000 1.4718 0.05605 0.05024 -0.0591 0.0131 1.0000 15.250 1.4794 0.05818 0.05242 -0.0591 0.0126 1.0000 15.500 1.4858 0.06050 0.05478 -0.0591 0.0120 1.0000 15.750 1.4924 0.06280 0.05712 -0.0591 0.0117 1.0000 16.000 1.4974 0.06534 0.05971 -0.0592 0.0113 1.0000 16.250 1.5037 0.06775 0.06217 -0.0594 0.0110 1.0000 16.500 1.5092 0.07033 0.06480 -0.0596 0.0107 1.0000 16.750 1.5151 0.07284 0.06737 -0.0599 0.0104 1.0000 17.000 1.5193 0.07562 0.07021 -0.0603 0.0102 1.0000 17.250 1.5243 0.07832 0.07296 -0.0607 0.0100 1.0000 17.500 1.5279 0.08126 0.07596 -0.0612 0.0098 1.0000 17.750 1.5316 0.08420 0.07896 -0.0617 0.0096 1.0000 18.000 1.5341 0.08735 0.08217 -0.0624 0.0094 1.0000 18.250 1.5365 0.09053 0.08541 -0.0631 0.0093 1.0000 18.500 1.5374 0.09397 0.08891 -0.0640 0.0091 1.0000 18.750 1.5392 0.09731 0.09232 -0.0649 0.0090 1.0000 19.000 1.5411 0.10068 0.09577 -0.0658 0.0089 1.0000 19.250 1.5426 0.10412 0.09929 -0.0669 0.0088 1.0000