XFOIL Version 6.96 Calculated polar for: CLARK W AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -9.250 -0.4002 0.09127 0.08595 -0.0432 1.0000 0.0504 -9.000 -0.4145 0.08728 0.08204 -0.0434 1.0000 0.0497 -8.500 -0.5148 0.07182 0.06683 -0.0464 1.0000 0.0470 -8.250 -0.5335 0.06691 0.06191 -0.0465 1.0000 0.0468 -8.000 -0.5448 0.05597 0.05064 -0.0541 0.9951 0.0466 -7.750 -0.5448 0.04475 0.03844 -0.0620 0.9862 0.0471 -7.500 -0.5215 0.04212 0.03566 -0.0639 0.9817 0.0479 -7.250 -0.4994 0.03910 0.03230 -0.0655 0.9761 0.0486 -7.000 -0.4733 0.03585 0.02858 -0.0677 0.9722 0.0491 -6.750 -0.4516 0.03344 0.02579 -0.0680 0.9660 0.0496 -6.500 -0.4232 0.03128 0.02325 -0.0694 0.9617 0.0504 -6.250 -0.3940 0.02946 0.02108 -0.0705 0.9577 0.0512 -6.000 -0.3683 0.02807 0.01939 -0.0706 0.9518 0.0526 -5.750 -0.3366 0.02671 0.01769 -0.0718 0.9478 0.0543 -5.500 -0.3025 0.02547 0.01622 -0.0734 0.9450 0.0557 -5.250 -0.2788 0.02461 0.01531 -0.0729 0.9380 0.0568 -5.000 -0.2471 0.02377 0.01439 -0.0739 0.9336 0.0582 -4.750 -0.2122 0.02295 0.01348 -0.0754 0.9305 0.0601 -4.500 -0.1862 0.02231 0.01272 -0.0752 0.9240 0.0622 -4.250 -0.1554 0.02166 0.01199 -0.0758 0.9189 0.0651 -4.000 -0.1203 0.02109 0.01143 -0.0774 0.9154 0.0701 -3.750 -0.0915 0.02059 0.01086 -0.0776 0.9097 0.0761 -3.500 -0.0625 0.02007 0.01035 -0.0779 0.9036 0.0846 -3.250 -0.0281 0.01948 0.00977 -0.0791 0.8996 0.1010 -3.000 -0.0001 0.01905 0.00943 -0.0792 0.8931 0.1216 -2.750 0.0301 0.01868 0.00912 -0.0796 0.8867 0.1472 -2.500 0.0658 0.01824 0.00879 -0.0810 0.8824 0.1796 -2.250 0.0908 0.01800 0.00868 -0.0804 0.8728 0.2122 -2.000 0.1253 0.01764 0.00846 -0.0814 0.8671 0.2534 -1.750 0.1511 0.01747 0.00836 -0.0808 0.8575 0.2848 -1.500 0.1844 0.01718 0.00809 -0.0814 0.8515 0.3150 -1.250 0.2105 0.01703 0.00795 -0.0808 0.8421 0.3395 -1.000 0.2430 0.01675 0.00768 -0.0813 0.8356 0.3656 -0.750 0.2693 0.01658 0.00754 -0.0808 0.8258 0.3903 -0.500 0.3017 0.01623 0.00725 -0.0813 0.8189 0.4200 -0.250 0.3264 0.01598 0.00713 -0.0805 0.8083 0.4547 0.000 0.3547 0.01535 0.00685 -0.0802 0.8006 0.5315 0.250 0.4385 0.01443 0.00694 -0.0902 0.7929 0.9944 0.500 0.4726 0.01435 0.00672 -0.0911 0.7830 1.0000 0.750 0.4978 0.01435 0.00661 -0.0903 0.7711 1.0000 1.000 0.5217 0.01438 0.00656 -0.0892 0.7582 1.0000 1.250 0.5466 0.01440 0.00649 -0.0884 0.7455 1.0000 1.500 0.5720 0.01442 0.00641 -0.0875 0.7324 1.0000 1.750 0.5975 0.01444 0.00634 -0.0867 0.7189 1.0000 2.000 0.6222 0.01448 0.00630 -0.0858 0.7042 1.0000 2.250 0.6461 0.01456 0.00630 -0.0847 0.6886 1.0000 2.500 0.6701 0.01464 0.00632 -0.0837 0.6724 1.0000 2.750 0.6941 0.01475 0.00634 -0.0826 0.6555 1.0000 3.000 0.7174 0.01488 0.00641 -0.0815 0.6378 1.0000 3.250 0.7406 0.01504 0.00650 -0.0803 0.6195 1.0000 3.500 0.7638 0.01521 0.00660 -0.0792 0.6009 1.0000 3.750 0.7869 0.01541 0.00673 -0.0781 0.5823 1.0000 4.000 0.8098 0.01564 0.00688 -0.0769 0.5638 1.0000 4.250 0.8327 0.01590 0.00706 -0.0758 0.5459 1.0000 4.500 0.8554 0.01618 0.00727 -0.0747 0.5286 1.0000 4.750 0.8780 0.01648 0.00752 -0.0736 0.5120 1.0000 5.000 0.9005 0.01681 0.00779 -0.0725 0.4964 1.0000 5.250 0.9230 0.01715 0.00809 -0.0714 0.4816 1.0000 5.500 0.9454 0.01751 0.00844 -0.0704 0.4676 1.0000 5.750 0.9678 0.01789 0.00880 -0.0693 0.4541 1.0000 6.000 0.9895 0.01829 0.00916 -0.0682 0.4398 1.0000 6.250 1.0103 0.01870 0.00953 -0.0669 0.4241 1.0000 6.500 1.0307 0.01913 0.00994 -0.0655 0.4085 1.0000 6.750 1.0512 0.01956 0.01035 -0.0642 0.3944 1.0000 7.000 1.0721 0.02000 0.01082 -0.0630 0.3820 1.0000 7.250 1.0926 0.02044 0.01133 -0.0618 0.3695 1.0000 7.500 1.1121 0.02089 0.01181 -0.0604 0.3557 1.0000 7.750 1.1297 0.02136 0.01230 -0.0587 0.3392 1.0000 8.000 1.1459 0.02185 0.01279 -0.0568 0.3209 1.0000 8.250 1.1614 0.02239 0.01332 -0.0549 0.3026 1.0000 8.500 1.1764 0.02295 0.01389 -0.0529 0.2849 1.0000 8.750 1.1911 0.02354 0.01452 -0.0509 0.2662 1.0000 9.000 1.2044 0.02419 0.01519 -0.0488 0.2462 1.0000 9.250 1.2150 0.02492 0.01590 -0.0462 0.2254 1.0000 9.500 1.2244 0.02578 0.01675 -0.0437 0.2024 1.0000 9.750 1.2317 0.02683 0.01771 -0.0410 0.1783 1.0000 10.000 1.2379 0.02804 0.01883 -0.0384 0.1546 1.0000 10.500 1.2451 0.03102 0.02165 -0.0332 0.1211 1.0000 10.750 1.2484 0.03265 0.02326 -0.0309 0.1093 1.0000 11.000 1.2523 0.03429 0.02497 -0.0287 0.0995 1.0000 11.250 1.2543 0.03612 0.02683 -0.0266 0.0918 1.0000 11.500 1.2568 0.03800 0.02877 -0.0248 0.0848 1.0000 11.750 1.2583 0.04002 0.03085 -0.0231 0.0795 1.0000 12.000 1.2605 0.04206 0.03299 -0.0216 0.0746 1.0000 12.250 1.2587 0.04451 0.03545 -0.0202 0.0710 1.0000 12.500 1.2615 0.04666 0.03774 -0.0191 0.0671 1.0000 12.750 1.2622 0.04908 0.04027 -0.0181 0.0639 1.0000 13.000 1.2602 0.05181 0.04303 -0.0173 0.0615 1.0000 13.250 1.2605 0.05441 0.04574 -0.0165 0.0589 1.0000 13.500 1.2613 0.05704 0.04851 -0.0160 0.0563 1.0000 13.750 1.2609 0.05984 0.05141 -0.0156 0.0542 1.0000 14.000 1.2593 0.06282 0.05444 -0.0153 0.0524 1.0000 14.250 1.2590 0.06573 0.05742 -0.0150 0.0506 1.0000 14.500 1.2596 0.06869 0.06057 -0.0149 0.0486 1.0000 14.750 1.2591 0.07180 0.06382 -0.0149 0.0468 1.0000 15.000 1.2584 0.07499 0.06710 -0.0151 0.0453 1.0000 15.250 1.2578 0.07815 0.07030 -0.0154 0.0440 1.0000 15.500 1.2575 0.08135 0.07358 -0.0155 0.0427 1.0000 15.750 1.2542 0.08523 0.07770 -0.0162 0.0413 1.0000 16.000 1.2507 0.08918 0.08183 -0.0171 0.0400 1.0000 16.250 1.2471 0.09318 0.08598 -0.0182 0.0389 1.0000 16.500 1.2440 0.09711 0.09003 -0.0193 0.0380 1.0000 16.750 1.2424 0.10078 0.09376 -0.0202 0.0371 1.0000 17.000 1.2437 0.10384 0.09682 -0.0208 0.0362 1.0000 17.250 1.2323 0.10968 0.10293 -0.0233 0.0356 1.0000 17.500 1.2195 0.11594 0.10945 -0.0263 0.0350 1.0000 17.750 1.2052 0.12270 0.11645 -0.0299 0.0344 1.0000 18.000 1.1890 0.13011 0.12409 -0.0340 0.0340 1.0000 18.250 1.1695 0.13863 0.13284 -0.0391 0.0337 1.0000 18.500 1.1426 0.14946 0.14390 -0.0460 0.0337 1.0000