XFOIL Version 6.96 Calculated polar for: NACA 63(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 -0.9806 0.09141 0.08793 -0.0668 1.0000 0.0114 -19.500 -0.9955 0.08558 0.08198 -0.0699 1.0000 0.0115 -19.250 -1.0091 0.08004 0.07635 -0.0729 1.0000 0.0115 -19.000 -1.0212 0.07486 0.07106 -0.0756 1.0000 0.0116 -18.750 -1.0319 0.07002 0.06613 -0.0781 1.0000 0.0117 -18.500 -1.0410 0.06553 0.06156 -0.0803 1.0000 0.0119 -18.250 -1.0463 0.06167 0.05762 -0.0822 1.0000 0.0120 -18.000 -1.0504 0.05805 0.05392 -0.0838 1.0000 0.0122 -17.750 -1.0533 0.05468 0.05048 -0.0853 1.0000 0.0124 -17.500 -1.0549 0.05156 0.04730 -0.0865 1.0000 0.0127 -17.250 -1.0546 0.04873 0.04439 -0.0876 1.0000 0.0127 -17.000 -1.0529 0.04615 0.04176 -0.0885 1.0000 0.0130 -16.750 -1.0504 0.04374 0.03929 -0.0892 1.0000 0.0133 -16.500 -1.0471 0.04149 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-0.1115 0.5638 0.4859 -1.250 0.3667 0.00719 0.00168 -0.1119 0.5596 0.4927 -1.000 0.3963 0.00721 0.00169 -0.1122 0.5560 0.4983 -0.750 0.4260 0.00723 0.00170 -0.1126 0.5521 0.5031 -0.500 0.4556 0.00725 0.00172 -0.1130 0.5475 0.5088 -0.250 0.4848 0.00729 0.00175 -0.1133 0.5430 0.5146 0.000 0.5141 0.00734 0.00178 -0.1136 0.5393 0.5200 0.250 0.5438 0.00736 0.00181 -0.1140 0.5358 0.5247 0.500 0.5732 0.00739 0.00185 -0.1144 0.5316 0.5297 0.750 0.6023 0.00744 0.00190 -0.1147 0.5271 0.5346 1.000 0.6312 0.00751 0.00194 -0.1149 0.5227 0.5388 1.250 0.6607 0.00754 0.00199 -0.1153 0.5190 0.5426 1.500 0.6898 0.00759 0.00205 -0.1156 0.5141 0.5471 1.750 0.7186 0.00766 0.00211 -0.1158 0.5090 0.5520 2.000 0.7473 0.00773 0.00218 -0.1160 0.5046 0.5567 2.250 0.7764 0.00778 0.00225 -0.1164 0.5004 0.5609 2.500 0.8053 0.00784 0.00232 -0.1166 0.4958 0.5656 2.750 0.8337 0.00793 0.00241 -0.1168 0.4910 0.5703 3.000 0.8622 0.00801 0.00249 -0.1170 0.4868 0.5747 3.250 0.8910 0.00807 0.00258 -0.1173 0.4823 0.5787 3.500 0.9193 0.00816 0.00268 -0.1175 0.4768 0.5839 3.750 0.9469 0.00827 0.00279 -0.1175 0.4707 0.5894 4.000 0.9752 0.00836 0.00289 -0.1177 0.4638 0.5944 4.250 1.0021 0.00852 0.00302 -0.1177 0.4548 0.5988 4.500 1.0301 0.00861 0.00314 -0.1178 0.4472 0.6039 4.750 1.0569 0.00876 0.00328 -0.1177 0.4391 0.6090 5.000 1.0841 0.00889 0.00342 -0.1177 0.4304 0.6139 5.250 1.1099 0.00909 0.00359 -0.1175 0.4188 0.6189 5.500 1.1350 0.00933 0.00379 -0.1172 0.4032 0.6248 5.750 1.1595 0.00959 0.00400 -0.1168 0.3866 0.6306 6.000 1.1830 0.00989 0.00424 -0.1162 0.3670 0.6353 6.250 1.2032 0.01037 0.00459 -0.1151 0.3376 0.6406 6.500 1.2194 0.01102 0.00506 -0.1133 0.2990 0.6466 6.750 1.2343 0.01171 0.00556 -0.1114 0.2637 0.6524 7.000 1.2500 0.01229 0.00603 -0.1096 0.2380 0.6580 7.250 1.2648 0.01283 0.00649 -0.1076 0.2155 0.6641 7.500 1.2745 0.01340 0.00697 -0.1046 0.1948 0.6701 7.750 1.2847 0.01401 0.00750 -0.1018 0.1764 0.6760 8.000 1.2937 0.01469 0.00812 -0.0990 0.1572 0.6827 8.250 1.3024 0.01542 0.00878 -0.0963 0.1404 0.6894 8.500 1.3098 0.01625 0.00954 -0.0936 0.1239 0.6952 8.750 1.3178 0.01710 0.01035 -0.0911 0.1101 0.7022 9.000 1.3264 0.01799 0.01121 -0.0888 0.0984 0.7093 9.250 1.3344 0.01897 0.01217 -0.0866 0.0871 0.7160 9.500 1.3429 0.01998 0.01317 -0.0846 0.0775 0.7233 9.750 1.3518 0.02103 0.01421 -0.0828 0.0693 0.7301 10.000 1.3604 0.02215 0.01534 -0.0811 0.0619 0.7374 10.250 1.3684 0.02337 0.01656 -0.0794 0.0548 0.7457 10.500 1.3770 0.02460 0.01780 -0.0779 0.0492 0.7531 10.750 1.3851 0.02591 0.01913 -0.0765 0.0443 0.7612 11.250 1.4022 0.02861 0.02189 -0.0739 0.0368 0.7779 11.500 1.4103 0.03006 0.02337 -0.0728 0.0341 0.7870 11.750 1.4193 0.03147 0.02484 -0.0718 0.0319 0.7974 12.000 1.4276 0.03297 0.02640 -0.0708 0.0304 0.8076 12.250 1.4364 0.03447 0.02796 -0.0699 0.0290 0.8191 12.500 1.4449 0.03603 0.02960 -0.0691 0.0278 0.8316 12.750 1.4526 0.03768 0.03132 -0.0682 0.0267 0.8463 13.000 1.4595 0.03940 0.03312 -0.0674 0.0256 0.8646 13.250 1.4662 0.04104 0.03488 -0.0664 0.0250 0.8938 13.500 1.4715 0.04257 0.03657 -0.0652 0.0243 1.0000 13.750 1.4790 0.04451 0.03856 -0.0648 0.0235 1.0000 14.000 1.4860 0.04655 0.04063 -0.0645 0.0227 1.0000 14.250 1.4924 0.04869 0.04281 -0.0642 0.0220 1.0000 14.500 1.5001 0.05075 0.04491 -0.0640 0.0215 1.0000 14.750 1.5078 0.05282 0.04703 -0.0639 0.0210 1.0000 15.000 1.5141 0.05509 0.04935 -0.0638 0.0203 1.0000 15.250 1.5205 0.05739 0.05169 -0.0638 0.0197 1.0000 15.500 1.5254 0.05992 0.05427 -0.0639 0.0191 1.0000 15.750 1.5308 0.06241 0.05680 -0.0640 0.0185 1.0000 16.000 1.5365 0.06492 0.05937 -0.0642 0.0181 1.0000 16.250 1.5424 0.06741 0.06192 -0.0644 0.0175 1.0000 16.500 1.5467 0.07018 0.06474 -0.0647 0.0169 1.0000 16.750 1.5509 0.07296 0.06757 -0.0651 0.0163 1.0000 17.000 1.5536 0.07600 0.07066 -0.0656 0.0157 1.0000 17.250 1.5581 0.07883 0.07354 -0.0661 0.0152 1.0000 17.500 1.5614 0.08186 0.07664 -0.0667 0.0146 1.0000 17.750 1.5644 0.08496 0.07980 -0.0674 0.0140 1.0000 18.000 1.5663 0.08827 0.08316 -0.0682 0.0135 1.0000 18.250 1.5679 0.09165 0.08659 -0.0691 0.0129 1.0000 18.500 1.5699 0.09498 0.08999 -0.0700 0.0124 1.0000 18.750 1.5709 0.09851 0.09358 -0.0710 0.0119 1.0000 19.000 1.5718 0.10205 0.09719 -0.0721 0.0114 1.0000 19.250 1.5713 0.10587 0.10107 -0.0734 0.0111 1.0000