XFOIL Version 6.96 Calculated polar for: LDS-2 AIRFOIL 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 ------ -------- --------- --------- -------- -------- -------- -15.750 -0.9590 0.06664 0.06410 -0.0536 1.0000 0.0082 -15.500 -0.9991 0.05566 0.05290 -0.0614 1.0000 0.0082 -15.250 -1.0251 0.04792 0.04498 -0.0670 1.0000 0.0081 -15.000 -1.0357 0.04302 0.03992 -0.0703 1.0000 0.0082 -14.750 -1.0464 0.03853 0.03527 -0.0730 1.0000 0.0082 -14.500 -1.0521 0.03519 0.03178 -0.0744 1.0000 0.0083 -14.250 -1.0573 0.03242 0.02887 -0.0746 1.0000 0.0083 -14.000 -1.0590 0.03039 0.02671 -0.0738 1.0000 0.0083 -13.750 -1.0614 0.02862 0.02481 -0.0720 1.0000 0.0084 -13.500 -1.0611 0.02731 0.02339 -0.0695 1.0000 0.0084 -13.250 -1.0611 0.02624 0.02221 -0.0662 1.0000 0.0085 -13.000 -1.0583 0.02526 0.02114 -0.0629 1.0000 0.0086 -12.750 -1.0505 0.02429 0.02005 -0.0604 1.0000 0.0086 -12.500 -1.0410 0.02340 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0.00148 -0.0399 0.4253 0.7837 2.750 0.5144 0.00673 0.00162 -0.0385 0.3902 0.8247 3.000 0.5349 0.00699 0.00181 -0.0370 0.3387 0.8665 3.250 0.5576 0.00730 0.00203 -0.0360 0.2934 0.9088 3.500 0.5895 0.00758 0.00224 -0.0370 0.2624 0.9388 3.750 0.6254 0.00796 0.00246 -0.0391 0.2248 0.9567 4.000 0.6618 0.00831 0.00268 -0.0412 0.1947 0.9677 4.250 0.6954 0.00862 0.00288 -0.0427 0.1730 0.9749 4.500 0.7278 0.00892 0.00308 -0.0439 0.1530 0.9812 4.750 0.7583 0.00920 0.00328 -0.0447 0.1370 0.9868 5.000 0.7890 0.00948 0.00348 -0.0455 0.1234 0.9917 5.250 0.8193 0.00977 0.00370 -0.0463 0.1104 0.9962 5.500 0.8510 0.01004 0.00391 -0.0474 0.1001 0.9991 5.750 0.8770 0.01031 0.00414 -0.0472 0.0918 1.0000 6.000 0.8983 0.01052 0.00433 -0.0460 0.0863 1.0000 6.250 0.9186 0.01079 0.00455 -0.0446 0.0795 1.0000 6.500 0.9400 0.01100 0.00476 -0.0434 0.0756 1.0000 6.750 0.9609 0.01125 0.00499 -0.0421 0.0713 1.0000 7.000 0.9815 0.01152 0.00523 -0.0408 0.0669 1.0000 7.250 1.0028 0.01174 0.00546 -0.0396 0.0642 1.0000 7.500 1.0233 0.01202 0.00573 -0.0383 0.0605 1.0000 7.750 1.0433 0.01232 0.00600 -0.0369 0.0569 1.0000 8.000 1.0642 0.01256 0.00626 -0.0357 0.0551 1.0000 8.250 1.0844 0.01283 0.00654 -0.0343 0.0526 1.0000 8.500 1.1038 0.01316 0.00685 -0.0329 0.0498 1.0000 8.750 1.1231 0.01347 0.00717 -0.0315 0.0475 1.0000 9.000 1.1429 0.01375 0.00747 -0.0301 0.0460 1.0000 9.250 1.1619 0.01406 0.00780 -0.0287 0.0442 1.0000 9.500 1.1798 0.01442 0.00815 -0.0270 0.0423 1.0000 9.750 1.1953 0.01478 0.00852 -0.0249 0.0405 1.0000 10.000 1.2109 0.01512 0.00888 -0.0229 0.0394 1.0000 10.250 1.2270 0.01545 0.00926 -0.0209 0.0383 1.0000 10.500 1.2428 0.01583 0.00966 -0.0190 0.0369 1.0000 10.750 1.2582 0.01626 0.01010 -0.0172 0.0356 1.0000 11.000 1.2729 0.01675 0.01060 -0.0153 0.0341 1.0000 11.250 1.2880 0.01724 0.01112 -0.0136 0.0330 1.0000 11.500 1.3040 0.01770 0.01162 -0.0120 0.0321 1.0000 11.750 1.3192 0.01822 0.01218 -0.0104 0.0312 1.0000 12.000 1.3339 0.01879 0.01279 -0.0089 0.0300 1.0000 12.250 1.3479 0.01944 0.01345 -0.0073 0.0290 1.0000 12.500 1.3606 0.02019 0.01422 -0.0057 0.0276 1.0000 12.750 1.3753 0.02083 0.01493 -0.0044 0.0271 1.0000 13.000 1.3892 0.02154 0.01569 -0.0031 0.0264 1.0000 13.250 1.4026 0.02232 0.01651 -0.0019 0.0255 1.0000 13.500 1.4151 0.02318 0.01741 -0.0006 0.0246 1.0000 13.750 1.4267 0.02415 0.01841 0.0006 0.0237 1.0000 14.000 1.4379 0.02517 0.01948 0.0018 0.0227 1.0000 14.250 1.4500 0.02613 0.02050 0.0029 0.0220 1.0000 14.500 1.4611 0.02721 0.02163 0.0039 0.0213 1.0000 14.750 1.4714 0.02838 0.02285 0.0048 0.0206 1.0000 15.000 1.4804 0.02968 0.02419 0.0058 0.0196 1.0000 15.250 1.4880 0.03112 0.02568 0.0067 0.0188 1.0000 15.500 1.4965 0.03254 0.02717 0.0075 0.0185 1.0000 15.750 1.5050 0.03397 0.02868 0.0082 0.0178 1.0000 16.000 1.5118 0.03557 0.03035 0.0089 0.0173 1.0000 16.250 1.5177 0.03732 0.03216 0.0095 0.0167 1.0000 16.500 1.5224 0.03921 0.03410 0.0100 0.0161 1.0000 16.750 1.5259 0.04126 0.03623 0.0104 0.0157 1.0000 17.000 1.5276 0.04357 0.03861 0.0107 0.0152 1.0000 17.250 1.5309 0.04578 0.04090 0.0109 0.0149 1.0000 17.500 1.5330 0.04818 0.04340 0.0109 0.0146 1.0000 17.750 1.5336 0.05081 0.04611 0.0108 0.0142 1.0000 18.000 1.5333 0.05361 0.04900 0.0106 0.0138 1.0000 18.250 1.5312 0.05670 0.05218 0.0102 0.0135 1.0000 18.500 1.5268 0.06016 0.05571 0.0096 0.0129 1.0000 18.750 1.5219 0.06377 0.05943 0.0088 0.0128 1.0000 19.000 1.5138 0.06792 0.06367 0.0077 0.0125 1.0000 19.250 1.5041 0.07243 0.06830 0.0063 0.0123 1.0000