XFOIL Version 6.96 Calculated polar for: NACA 66(2)-215 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 ------ -------- --------- --------- -------- -------- -------- -18.750 -0.9993 0.08396 0.08137 -0.0639 1.0000 0.0100 -18.500 -1.0401 0.07319 0.07034 -0.0699 1.0000 0.0099 -18.250 -1.0508 0.06785 0.06489 -0.0728 1.0000 0.0100 -18.000 -1.0691 0.06175 0.05862 -0.0757 1.0000 0.0100 -17.750 -1.0776 0.05742 0.05417 -0.0775 1.0000 0.0100 -17.500 -1.0836 0.05364 0.05029 -0.0787 1.0000 0.0101 -17.250 -1.0866 0.05046 0.04700 -0.0795 1.0000 0.0101 -17.000 -1.0809 0.04842 0.04491 -0.0799 1.0000 0.0103 -16.750 -1.0914 0.04480 0.04112 -0.0800 1.0000 0.0103 -16.500 -1.0854 0.04301 0.03928 -0.0800 1.0000 0.0104 -16.000 -1.0788 0.03869 0.03477 -0.0799 0.9787 0.0106 -15.750 -1.0585 0.03643 0.03236 -0.0834 0.9669 0.0108 -15.500 -1.0343 0.03443 0.03023 -0.0870 0.9563 0.0109 -15.250 -1.0141 0.03271 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0.00144 -0.0393 0.7332 0.7095 -0.750 0.0862 0.00578 0.00144 -0.0397 0.7319 0.7155 -0.500 0.1149 0.00580 0.00149 -0.0400 0.7307 0.7235 0.000 0.1732 0.00586 0.00153 -0.0409 0.7285 0.7307 0.250 0.2025 0.00586 0.00154 -0.0414 0.7272 0.7318 0.500 0.2316 0.00586 0.00154 -0.0418 0.7246 0.7328 0.750 0.2604 0.00585 0.00153 -0.0422 0.7211 0.7339 1.000 0.2892 0.00584 0.00153 -0.0426 0.7175 0.7351 1.250 0.3175 0.00584 0.00153 -0.0428 0.7119 0.7364 1.500 0.3456 0.00583 0.00152 -0.0430 0.7031 0.7378 1.750 0.3738 0.00584 0.00153 -0.0433 0.6962 0.7392 2.000 0.4019 0.00585 0.00155 -0.0435 0.6874 0.7406 2.250 0.4296 0.00588 0.00156 -0.0436 0.6752 0.7419 2.500 0.4548 0.00597 0.00157 -0.0432 0.6444 0.7433 2.750 0.4679 0.00659 0.00175 -0.0405 0.5406 0.7450 3.000 0.4782 0.00742 0.00213 -0.0374 0.4389 0.7467 3.250 0.4886 0.00820 0.00249 -0.0345 0.3421 0.7482 3.500 0.4979 0.00897 0.00286 -0.0314 0.2477 0.7499 3.750 0.5087 0.00963 0.00320 -0.0285 0.1708 0.7517 4.000 0.5216 0.01017 0.00350 -0.0260 0.1123 0.7536 4.250 0.5336 0.01063 0.00378 -0.0233 0.0682 0.7555 4.500 0.5474 0.01101 0.00405 -0.0208 0.0409 0.7575 4.750 0.5664 0.01128 0.00428 -0.0194 0.0344 0.7594 5.000 0.5867 0.01151 0.00451 -0.0183 0.0315 0.7614 5.250 0.6066 0.01178 0.00477 -0.0171 0.0291 0.7634 5.500 0.6261 0.01208 0.00506 -0.0159 0.0269 0.7652 5.750 0.6466 0.01231 0.00532 -0.0148 0.0260 0.7673 6.000 0.6669 0.01257 0.00560 -0.0138 0.0249 0.7694 6.250 0.6869 0.01285 0.00590 -0.0127 0.0237 0.7715 6.500 0.7063 0.01317 0.00622 -0.0116 0.0224 0.7738 6.750 0.7250 0.01353 0.00659 -0.0104 0.0213 0.7762 7.000 0.7455 0.01382 0.00690 -0.0095 0.0206 0.7785 7.250 0.7655 0.01414 0.00724 -0.0085 0.0199 0.7806 7.500 0.7851 0.01447 0.00759 -0.0075 0.0191 0.7829 7.750 0.8042 0.01482 0.00797 -0.0064 0.0182 0.7855 8.000 0.8227 0.01522 0.00838 -0.0053 0.0173 0.7882 8.250 0.8414 0.01562 0.00881 -0.0042 0.0166 0.7910 8.500 0.8605 0.01601 0.00922 -0.0033 0.0160 0.7939 8.750 0.8791 0.01643 0.00967 -0.0022 0.0156 0.7966 9.000 0.8978 0.01684 0.01011 -0.0013 0.0150 0.7994 9.250 0.9156 0.01730 0.01060 -0.0001 0.0144 0.8027 9.500 0.9331 0.01779 0.01111 0.0010 0.0140 0.8062 9.750 0.9493 0.01837 0.01172 0.0022 0.0134 0.8100 10.000 0.9665 0.01891 0.01230 0.0033 0.0133 0.8134 10.250 0.9834 0.01944 0.01289 0.0044 0.0130 0.8169 10.500 0.9996 0.02003 0.01354 0.0056 0.0129 0.8209 10.750 1.0159 0.02062 0.01418 0.0067 0.0126 0.8250 11.000 1.0323 0.02123 0.01484 0.0077 0.0122 0.8288 11.250 1.0488 0.02181 0.01546 0.0088 0.0119 0.8328 11.500 1.0641 0.02246 0.01618 0.0099 0.0118 0.8374 11.750 1.0798 0.02311 0.01687 0.0109 0.0114 0.8422 12.000 1.0943 0.02386 0.01766 0.0121 0.0112 0.8467 12.250 1.1080 0.02464 0.01851 0.0133 0.0111 0.8520 12.500 1.1209 0.02549 0.01944 0.0145 0.0109 0.8577 12.750 1.1326 0.02644 0.02045 0.0158 0.0107 0.8634 13.000 1.1424 0.02752 0.02163 0.0173 0.0105 0.8704 13.500 1.1653 0.02944 0.02373 0.0198 0.0104 0.8867 13.750 1.1761 0.03045 0.02484 0.0211 0.0102 0.8958 14.000 1.1862 0.03152 0.02602 0.0224 0.0102 0.9067 14.250 1.1943 0.03273 0.02735 0.0238 0.0101 0.9188 14.500 1.2033 0.03393 0.02866 0.0250 0.0100 0.9332 14.750 1.2151 0.03523 0.03009 0.0254 0.0100 0.9531 15.000 1.2346 0.03690 0.03189 0.0236 0.0098 0.9807 15.250 1.2416 0.03835 0.03342 0.0247 0.0098 1.0000 15.500 1.2492 0.03996 0.03510 0.0254 0.0097 1.0000 15.750 1.2557 0.04168 0.03690 0.0261 0.0096 1.0000 16.000 1.2609 0.04358 0.03890 0.0267 0.0095 1.0000 16.250 1.2691 0.04524 0.04063 0.0271 0.0094 1.0000 16.500 1.2744 0.04722 0.04269 0.0275 0.0092 1.0000 16.750 1.2748 0.04978 0.04536 0.0280 0.0093 1.0000 17.000 1.2780 0.05210 0.04776 0.0281 0.0092 1.0000 17.250 1.2822 0.05440 0.05015 0.0281 0.0091 1.0000 17.500 1.2838 0.05707 0.05291 0.0280 0.0090 1.0000 17.750 1.2836 0.06004 0.05598 0.0276 0.0089 1.0000 18.000 1.2835 0.06312 0.05915 0.0271 0.0089 1.0000 18.250 1.2805 0.06666 0.06281 0.0263 0.0088 1.0000 18.500 1.2779 0.07033 0.06658 0.0252 0.0087 1.0000 18.750 1.2701 0.07487 0.07125 0.0238 0.0087 1.0000 19.000 1.2644 0.07928 0.07578 0.0220 0.0087 1.0000 19.250 1.2564 0.08420 0.08081 0.0199 0.0086 1.0000