XFOIL Version 6.96 Calculated polar for: CLARK Y AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -11.000 -0.3991 0.10855 0.10470 -0.0373 1.0000 0.0283 -10.750 -0.4131 0.10067 0.09685 -0.0415 1.0000 0.0292 -10.500 -0.4187 0.09546 0.09168 -0.0438 1.0000 0.0297 -10.250 -0.4148 0.09285 0.08910 -0.0444 1.0000 0.0300 -10.000 -0.4155 0.08932 0.08560 -0.0456 1.0000 0.0303 -9.750 -0.4199 0.08535 0.08167 -0.0469 1.0000 0.0305 -9.500 -0.4281 0.08133 0.07771 -0.0480 1.0000 0.0308 -9.250 -0.4414 0.07744 0.07389 -0.0485 1.0000 0.0311 -9.000 -0.5389 0.05070 0.04695 -0.0702 0.9886 0.0307 -8.750 -0.5278 0.04461 0.04051 -0.0762 0.9817 0.0316 -8.500 -0.5181 0.03875 0.03412 -0.0798 0.9735 0.0325 -8.250 -0.5015 0.03390 0.02868 -0.0823 0.9677 0.0333 -8.000 -0.4817 0.03065 0.02489 -0.0834 0.9610 0.0344 -7.750 -0.4552 0.02808 0.02177 -0.0849 0.9570 0.0354 -7.500 -0.4319 0.02623 0.01955 -0.0850 0.9504 0.0358 -7.250 -0.4054 0.02437 0.01748 -0.0857 0.9452 0.0364 -7.000 -0.3749 0.02307 0.01602 -0.0868 0.9416 0.0371 -6.750 -0.3498 0.02218 0.01503 -0.0867 0.9344 0.0380 -6.500 -0.3207 0.02126 0.01397 -0.0872 0.9291 0.0390 -6.250 -0.2910 0.02029 0.01282 -0.0878 0.9244 0.0400 -6.000 -0.2654 0.01941 0.01179 -0.0875 0.9166 0.0407 -5.750 -0.2356 0.01854 0.01078 -0.0879 0.9115 0.0414 -5.500 -0.2093 0.01783 0.00994 -0.0876 0.9041 0.0422 -5.250 -0.1811 0.01716 0.00916 -0.0877 0.8977 0.0429 -5.000 -0.1541 0.01645 0.00841 -0.0876 0.8910 0.0440 -4.750 -0.1275 0.01590 0.00785 -0.0874 0.8834 0.0455 -4.500 -0.0995 0.01543 0.00733 -0.0873 0.8772 0.0470 -4.250 -0.0733 0.01500 0.00686 -0.0870 0.8689 0.0485 -4.000 -0.0452 0.01457 0.00636 -0.0869 0.8626 0.0501 -3.750 -0.0191 0.01423 0.00595 -0.0865 0.8540 0.0517 -3.500 0.0087 0.01382 0.00552 -0.0864 0.8476 0.0543 -3.250 0.0349 0.01355 0.00523 -0.0860 0.8389 0.0583 -3.000 0.0628 0.01325 0.00490 -0.0859 0.8319 0.0644 -2.750 0.0892 0.01299 0.00464 -0.0855 0.8222 0.0746 -2.500 0.1161 0.01269 0.00435 -0.0851 0.8128 0.0905 -2.250 0.1430 0.01240 0.00410 -0.0848 0.8027 0.1120 -2.000 0.1691 0.01213 0.00393 -0.0845 0.7918 0.1432 -1.750 0.1955 0.01185 0.00377 -0.0841 0.7816 0.1908 -1.500 0.2217 0.01157 0.00365 -0.0838 0.7712 0.2491 -1.250 0.2477 0.01135 0.00356 -0.0834 0.7593 0.2987 -1.000 0.2732 0.01108 0.00346 -0.0829 0.7476 0.3611 -0.750 0.2976 0.01069 0.00339 -0.0822 0.7373 0.4637 -0.500 0.3200 0.01022 0.00340 -0.0810 0.7273 0.6001 -0.250 0.3414 0.00982 0.00345 -0.0791 0.7176 0.7430 0.250 0.4236 0.00964 0.00350 -0.0832 0.6966 0.9672 0.500 0.4701 0.00968 0.00344 -0.0870 0.6857 0.9947 0.750 0.5017 0.00975 0.00338 -0.0878 0.6743 1.0000 1.000 0.5260 0.00983 0.00337 -0.0871 0.6622 1.0000 1.250 0.5503 0.00992 0.00337 -0.0863 0.6495 1.0000 1.500 0.5745 0.01003 0.00339 -0.0855 0.6371 1.0000 1.750 0.5988 0.01014 0.00342 -0.0847 0.6246 1.0000 2.000 0.6230 0.01026 0.00345 -0.0839 0.6112 1.0000 2.250 0.6471 0.01040 0.00350 -0.0831 0.5965 1.0000 2.500 0.6711 0.01055 0.00357 -0.0822 0.5809 1.0000 2.750 0.6951 0.01071 0.00365 -0.0814 0.5649 1.0000 3.000 0.7190 0.01089 0.00374 -0.0806 0.5489 1.0000 3.250 0.7429 0.01109 0.00386 -0.0797 0.5320 1.0000 3.500 0.7664 0.01130 0.00399 -0.0789 0.5138 1.0000 3.750 0.7898 0.01154 0.00414 -0.0780 0.4947 1.0000 4.000 0.8129 0.01180 0.00431 -0.0770 0.4759 1.0000 4.250 0.8361 0.01207 0.00450 -0.0761 0.4573 1.0000 4.500 0.8591 0.01235 0.00471 -0.0753 0.4385 1.0000 4.750 0.8819 0.01266 0.00494 -0.0743 0.4206 1.0000 5.000 0.9045 0.01299 0.00519 -0.0734 0.4038 1.0000 5.250 0.9268 0.01334 0.00546 -0.0724 0.3869 1.0000 5.500 0.9488 0.01372 0.00575 -0.0715 0.3708 1.0000 5.750 0.9706 0.01410 0.00606 -0.0705 0.3551 1.0000 6.000 0.9928 0.01448 0.00638 -0.0696 0.3413 1.0000 6.250 1.0154 0.01484 0.00671 -0.0687 0.3307 1.0000 6.500 1.0378 0.01521 0.00707 -0.0679 0.3218 1.0000 6.750 1.0610 0.01553 0.00742 -0.0671 0.3128 1.0000 7.000 1.0829 0.01592 0.00780 -0.0662 0.3043 1.0000 7.250 1.1060 0.01623 0.00817 -0.0655 0.2958 1.0000 7.500 1.1279 0.01661 0.00858 -0.0646 0.2874 1.0000 7.750 1.1498 0.01697 0.00898 -0.0637 0.2774 1.0000 8.000 1.1714 0.01733 0.00939 -0.0627 0.2667 1.0000 8.250 1.1917 0.01774 0.00982 -0.0616 0.2529 1.0000 8.500 1.2108 0.01819 0.01027 -0.0603 0.2355 1.0000 8.750 1.2278 0.01875 0.01076 -0.0588 0.2136 1.0000 9.000 1.2423 0.01941 0.01133 -0.0569 0.1887 1.0000 9.250 1.2544 0.02020 0.01201 -0.0547 0.1662 1.0000 9.500 1.2651 0.02111 0.01283 -0.0524 0.1462 1.0000 9.750 1.2765 0.02203 0.01368 -0.0503 0.1304 1.0000 10.000 1.2881 0.02296 0.01458 -0.0483 0.1180 1.0000 10.250 1.3006 0.02384 0.01547 -0.0465 0.1083 1.0000 10.500 1.3127 0.02476 0.01642 -0.0447 0.1007 1.0000 10.750 1.3231 0.02581 0.01749 -0.0429 0.0931 1.0000 11.000 1.3348 0.02680 0.01854 -0.0413 0.0860 1.0000 11.250 1.3442 0.02799 0.01975 -0.0396 0.0794 1.0000 11.500 1.3548 0.02911 0.02093 -0.0381 0.0716 1.0000 11.750 1.3635 0.03042 0.02226 -0.0365 0.0620 1.0000 12.000 1.3695 0.03199 0.02383 -0.0349 0.0497 1.0000 12.250 1.3701 0.03406 0.02581 -0.0331 0.0327 1.0000 12.500 1.3679 0.03648 0.02816 -0.0314 0.0246 1.0000 12.750 1.3678 0.03881 0.03055 -0.0300 0.0216 1.0000 13.000 1.3679 0.04122 0.03304 -0.0289 0.0199 1.0000 13.250 1.3663 0.04388 0.03579 -0.0279 0.0187 1.0000 13.500 1.3671 0.04640 0.03845 -0.0271 0.0179 1.0000 13.750 1.3662 0.04917 0.04136 -0.0266 0.0172 1.0000 14.000 1.3640 0.05219 0.04453 -0.0262 0.0167 1.0000 14.250 1.3602 0.05552 0.04801 -0.0261 0.0162 1.0000 14.500 1.3546 0.05920 0.05183 -0.0262 0.0159 1.0000 14.750 1.3474 0.06326 0.05603 -0.0267 0.0156 1.0000 15.000 1.3382 0.06776 0.06068 -0.0275 0.0153 1.0000 15.250 1.3286 0.07247 0.06552 -0.0285 0.0151 1.0000 15.500 1.3212 0.07701 0.07022 -0.0296 0.0149 1.0000 15.750 1.3128 0.08183 0.07520 -0.0310 0.0147 1.0000 16.000 1.3038 0.08685 0.08037 -0.0325 0.0145 1.0000 16.250 1.2942 0.09206 0.08572 -0.0342 0.0143 1.0000 16.500 1.2845 0.09738 0.09118 -0.0361 0.0141 1.0000