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 = 0.500 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -19.000 -0.8045 0.10280 0.09928 -0.0683 1.0000 0.0185 -18.750 -0.8277 0.09491 0.09123 -0.0727 1.0000 0.0185 -18.500 -0.8448 0.08828 0.08445 -0.0764 1.0000 0.0186 -18.250 -0.8592 0.08223 0.07825 -0.0798 1.0000 0.0189 -18.000 -0.8705 0.07700 0.07289 -0.0826 1.0000 0.0190 -17.750 -0.8799 0.07212 0.06785 -0.0851 1.0000 0.0192 -17.500 -0.8855 0.06803 0.06364 -0.0871 1.0000 0.0193 -17.250 -0.8901 0.06430 0.05984 -0.0888 1.0000 0.0194 -17.000 -0.8928 0.06090 0.05638 -0.0903 1.0000 0.0196 -16.750 -0.8947 0.05773 0.05314 -0.0915 1.0000 0.0197 -16.500 -0.8947 0.05487 0.05022 -0.0926 1.0000 0.0199 -16.250 -0.8942 0.05218 0.04746 -0.0934 1.0000 0.0201 -16.000 -0.8915 0.04980 0.04502 -0.0941 1.0000 0.0204 -15.750 -0.8893 0.04749 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-0.1020 0.6858 0.0553 -6.000 -0.1881 0.01225 0.00477 -0.1021 0.6804 0.0613 -5.750 -0.1615 0.01200 0.00452 -0.1022 0.6748 0.0692 -5.500 -0.1349 0.01175 0.00428 -0.1023 0.6695 0.0796 -5.250 -0.1078 0.01148 0.00405 -0.1026 0.6645 0.0944 -5.000 -0.0805 0.01119 0.00382 -0.1029 0.6590 0.1151 -4.500 -0.0261 0.01047 0.00333 -0.1036 0.6485 0.1873 -4.250 0.0016 0.00993 0.00303 -0.1044 0.6432 0.2528 -4.000 0.0296 0.00930 0.00272 -0.1052 0.6379 0.3429 -3.750 0.0583 0.00893 0.00260 -0.1060 0.6333 0.4278 -3.500 0.0877 0.00887 0.00257 -0.1064 0.6289 0.4549 -3.250 0.1170 0.00883 0.00255 -0.1068 0.6242 0.4746 -3.000 0.1461 0.00883 0.00253 -0.1071 0.6196 0.4903 -2.750 0.1750 0.00885 0.00252 -0.1074 0.6153 0.5023 -2.500 0.2044 0.00885 0.00255 -0.1077 0.6113 0.5173 -2.250 0.2337 0.00888 0.00259 -0.1081 0.6071 0.5319 -2.000 0.2628 0.00892 0.00259 -0.1084 0.6028 0.5389 -1.750 0.2917 0.00897 0.00256 -0.1086 0.5989 0.5423 -1.500 0.3208 0.00898 0.00256 -0.1089 0.5953 0.5460 -1.250 0.3500 0.00899 0.00257 -0.1093 0.5916 0.5498 -1.000 0.3790 0.00901 0.00258 -0.1096 0.5877 0.5530 -0.750 0.4079 0.00905 0.00258 -0.1098 0.5839 0.5557 -0.500 0.4366 0.00911 0.00259 -0.1101 0.5802 0.5586 -0.250 0.4658 0.00914 0.00261 -0.1104 0.5768 0.5616 0.000 0.4948 0.00916 0.00264 -0.1107 0.5734 0.5645 0.250 0.5237 0.00919 0.00268 -0.1110 0.5701 0.5675 0.500 0.5524 0.00924 0.00273 -0.1113 0.5669 0.5706 0.750 0.5810 0.00931 0.00277 -0.1115 0.5639 0.5739 1.000 0.6098 0.00937 0.00283 -0.1118 0.5612 0.5773 1.250 0.6388 0.00942 0.00289 -0.1122 0.5585 0.5805 1.500 0.6676 0.00946 0.00296 -0.1125 0.5557 0.5838 1.750 0.6963 0.00952 0.00304 -0.1127 0.5529 0.5873 2.000 0.7248 0.00958 0.00313 -0.1130 0.5500 0.5912 2.250 0.7531 0.00967 0.00321 -0.1132 0.5472 0.5953 2.500 0.7814 0.00978 0.00330 -0.1134 0.5446 0.5993 2.750 0.8100 0.00982 0.00341 -0.1137 0.5420 0.6034 3.000 0.8384 0.00988 0.00353 -0.1139 0.5386 0.6081 3.250 0.8664 0.00996 0.00363 -0.1140 0.5347 0.6129 3.500 0.8942 0.01006 0.00374 -0.1142 0.5311 0.6175 3.750 0.9219 0.01017 0.00387 -0.1143 0.5282 0.6218 4.000 0.9499 0.01025 0.00402 -0.1145 0.5256 0.6266 4.250 0.9780 0.01033 0.00416 -0.1146 0.5226 0.6319 4.500 1.0054 0.01042 0.00429 -0.1147 0.5181 0.6370 4.750 1.0314 0.01054 0.00442 -0.1145 0.5118 0.6419 5.000 1.0578 0.01063 0.00457 -0.1144 0.5049 0.6474 5.250 1.0830 0.01076 0.00471 -0.1140 0.4962 0.6532 5.500 1.1083 0.01088 0.00487 -0.1137 0.4872 0.6586 5.750 1.1332 0.01102 0.00504 -0.1133 0.4794 0.6644 6.000 1.1583 0.01117 0.00523 -0.1129 0.4716 0.6707 6.500 1.2016 0.01161 0.00567 -0.1110 0.4388 0.6834 6.750 1.2193 0.01195 0.00595 -0.1094 0.4112 0.6905 7.000 1.2284 0.01256 0.00638 -0.1063 0.3714 0.6971 7.250 1.2310 0.01329 0.00697 -0.1021 0.3375 0.7039 7.500 1.2333 0.01418 0.00771 -0.0981 0.3035 0.7112 7.750 1.2348 0.01517 0.00856 -0.0942 0.2701 0.7179 8.000 1.2359 0.01624 0.00951 -0.0905 0.2390 0.7254 8.250 1.2370 0.01741 0.01056 -0.0870 0.2110 0.7330 8.500 1.2396 0.01859 0.01168 -0.0840 0.1875 0.7404 8.750 1.2424 0.01985 0.01287 -0.0812 0.1659 0.7486 9.000 1.2457 0.02118 0.01414 -0.0787 0.1457 0.7564 9.250 1.2473 0.02268 0.01557 -0.0762 0.1266 0.7651 9.500 1.2505 0.02419 0.01704 -0.0740 0.1097 0.7738 9.750 1.2544 0.02570 0.01854 -0.0721 0.0957 0.7839 10.000 1.2587 0.02727 0.02009 -0.0703 0.0834 0.7938 10.250 1.2644 0.02880 0.02163 -0.0688 0.0739 0.8045 10.500 1.2700 0.03037 0.02322 -0.0673 0.0655 0.8154 10.750 1.2757 0.03197 0.02485 -0.0659 0.0583 0.8274 11.000 1.2809 0.03365 0.02656 -0.0646 0.0518 0.8408 11.250 1.2870 0.03524 0.02821 -0.0633 0.0471 0.8560 11.750 1.2958 0.03846 0.03160 -0.0603 0.0391 0.9101 12.000 1.3017 0.04009 0.03331 -0.0593 0.0362 1.0000 12.250 1.3099 0.04190 0.03515 -0.0588 0.0337 1.0000 12.500 1.3176 0.04380 0.03707 -0.0583 0.0314 1.0000 12.750 1.3257 0.04571 0.03901 -0.0579 0.0296 1.0000 13.000 1.3336 0.04768 0.04101 -0.0576 0.0280 1.0000 13.250 1.3407 0.04974 0.04311 -0.0573 0.0265 1.0000 13.500 1.3485 0.05178 0.04520 -0.0571 0.0252 1.0000 13.750 1.3564 0.05385 0.04731 -0.0569 0.0241 1.0000 14.000 1.3626 0.05614 0.04963 -0.0568 0.0229 1.0000 14.250 1.3696 0.05836 0.05190 -0.0567 0.0220 1.0000 14.500 1.3766 0.06062 0.05423 -0.0567 0.0211 1.0000 14.750 1.3833 0.06294 0.05660 -0.0567 0.0202 1.0000 15.000 1.3884 0.06550 0.05920 -0.0568 0.0194 1.0000 15.250 1.3944 0.06798 0.06174 -0.0570 0.0187 1.0000 15.500 1.4002 0.07054 0.06437 -0.0572 0.0180 1.0000 15.750 1.4058 0.07312 0.06702 -0.0575 0.0174 1.0000 16.000 1.4101 0.07594 0.06989 -0.0579 0.0168 1.0000 16.250 1.4139 0.07884 0.07285 -0.0583 0.0163 1.0000 16.500 1.4174 0.08183 0.07591 -0.0588 0.0159 1.0000 16.750 1.4220 0.08471 0.07886 -0.0594 0.0154 1.0000 17.000 1.4253 0.08779 0.08202 -0.0600 0.0149 1.0000 17.250 1.4288 0.09087 0.08518 -0.0607 0.0145 1.0000 17.500 1.4309 0.09419 0.08856 -0.0616 0.0142 1.0000 17.750 1.4328 0.09758 0.09201 -0.0625 0.0138 1.0000 18.000 1.4326 0.10132 0.09583 -0.0636 0.0135 1.0000 18.250 1.4343 0.10479 0.09938 -0.0646 0.0133 1.0000 18.500 1.4352 0.10842 0.10310 -0.0658 0.0131 1.0000 18.750 1.4363 0.11202 0.10679 -0.0671 0.0128 1.0000 19.000 1.4363 0.11588 0.11074 -0.0685 0.0126 1.0000 19.250 1.4365 0.11969 0.11464 -0.0700 0.0124 1.0000