CLARK YM-15 AIRFOIL (clarym15-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: CLARK YM-15 AIRFOIL (clarym15-il) Reynolds number: 50,000 Max Cl/Cd: 31.01 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-clarym15-il-50000-n5.txt Download as CSV file: xf-clarym15-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: CLARK YM-15 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.3666 0.10299 0.09535 -0.0496 1.0000 0.0853
-10.000 -0.3768 0.09915 0.09160 -0.0499 1.0000 0.0847
-9.750 -0.3911 0.09516 0.08771 -0.0501 1.0000 0.0842
-9.500 -0.4097 0.09100 0.08367 -0.0502 1.0000 0.0837
-9.250 -0.4360 0.08641 0.07919 -0.0502 1.0000 0.0831
-9.000 -0.4832 0.08001 0.07290 -0.0513 1.0000 0.0820
-8.750 -0.5421 0.07411 0.06703 -0.0498 1.0000 0.0808
-8.500 -0.5852 0.06870 0.06149 -0.0480 1.0000 0.0802
-8.250 -0.6102 0.06445 0.05705 -0.0460 1.0000 0.0801
-8.000 -0.6084 0.06057 0.05294 -0.0470 0.9959 0.0810
-7.750 -0.5940 0.05658 0.04862 -0.0496 0.9886 0.0827
-7.500 -0.5774 0.05246 0.04403 -0.0523 0.9818 0.0847
-7.250 -0.5615 0.04865 0.03969 -0.0537 0.9742 0.0865
-7.000 -0.5394 0.04514 0.03555 -0.0555 0.9679 0.0882
-6.750 -0.5162 0.04266 0.03267 -0.0563 0.9609 0.0899
-6.500 -0.4845 0.04114 0.03105 -0.0582 0.9558 0.0926
-6.250 -0.4611 0.03972 0.02942 -0.0584 0.9480 0.0962
-6.000 -0.4300 0.03794 0.02715 -0.0599 0.9424 0.1008
-5.750 -0.4030 0.03668 0.02584 -0.0605 0.9357 0.1044
-5.500 -0.3736 0.03559 0.02463 -0.0613 0.9290 0.1092
-5.250 -0.3378 0.03441 0.02321 -0.0632 0.9244 0.1168
-5.000 -0.3155 0.03369 0.02250 -0.0627 0.9158 0.1235
-4.750 -0.2819 0.03282 0.02156 -0.0641 0.9102 0.1337
-4.500 -0.2538 0.03218 0.02082 -0.0644 0.9033 0.1456
-4.000 -0.1883 0.03109 0.01979 -0.0669 0.8913 0.1790
-3.750 -0.1670 0.03076 0.01950 -0.0661 0.8822 0.1965
-3.500 -0.1322 0.03027 0.01904 -0.0676 0.8765 0.2222
-3.250 -0.1048 0.02990 0.01874 -0.0678 0.8691 0.2488
-3.000 -0.0759 0.02952 0.01840 -0.0681 0.8619 0.2815
-2.750 -0.0388 0.02900 0.01801 -0.0699 0.8573 0.3225
-2.500 -0.0208 0.02884 0.01796 -0.0684 0.8473 0.3566
-2.250 0.0131 0.02838 0.01770 -0.0695 0.8419 0.4059
-2.000 0.0341 0.02816 0.01772 -0.0684 0.8330 0.4559
-1.750 0.0620 0.02773 0.01765 -0.0680 0.8264 0.5309
-1.500 0.0872 0.02729 0.01773 -0.0665 0.8200 0.6371
-1.250 0.1102 0.02717 0.01806 -0.0640 0.8113 0.7644
-1.000 0.1761 0.02696 0.01788 -0.0689 0.8068 0.8958
-0.750 0.2404 0.02687 0.01758 -0.0751 0.7960 0.9650
-0.500 0.3235 0.02619 0.01659 -0.0847 0.7890 1.0000
-0.250 0.3375 0.02617 0.01640 -0.0824 0.7751 1.0000
0.000 0.3569 0.02613 0.01619 -0.0808 0.7635 1.0000
0.250 0.3858 0.02594 0.01582 -0.0807 0.7549 1.0000
0.500 0.3997 0.02614 0.01590 -0.0784 0.7425 1.0000
0.750 0.4312 0.02591 0.01551 -0.0785 0.7346 1.0000
1.000 0.4472 0.02609 0.01559 -0.0764 0.7222 1.0000
1.250 0.4665 0.02622 0.01561 -0.0748 0.7107 1.0000
1.500 0.4980 0.02600 0.01527 -0.0748 0.7022 1.0000
1.750 0.5140 0.02625 0.01544 -0.0727 0.6891 1.0000
2.000 0.5369 0.02631 0.01541 -0.0716 0.6777 1.0000
2.250 0.5669 0.02614 0.01514 -0.0713 0.6679 1.0000
2.500 0.5847 0.02638 0.01533 -0.0695 0.6544 1.0000
2.750 0.6071 0.02650 0.01538 -0.0683 0.6419 1.0000
3.000 0.6382 0.02631 0.01509 -0.0682 0.6317 1.0000
3.250 0.6583 0.02653 0.01526 -0.0667 0.6179 1.0000
3.500 0.6788 0.02676 0.01546 -0.0653 0.6043 1.0000
3.750 0.7025 0.02691 0.01555 -0.0643 0.5913 1.0000
4.000 0.7309 0.02689 0.01544 -0.0639 0.5796 1.0000
4.250 0.7535 0.02713 0.01564 -0.0628 0.5662 1.0000
4.500 0.7739 0.02750 0.01598 -0.0615 0.5526 1.0000
4.750 0.7974 0.02780 0.01622 -0.0606 0.5403 1.0000
5.000 0.8271 0.02787 0.01620 -0.0605 0.5297 1.0000
5.250 0.8448 0.02846 0.01679 -0.0590 0.5166 1.0000
5.500 0.8664 0.02894 0.01726 -0.0580 0.5053 1.0000
5.750 0.8951 0.02917 0.01742 -0.0579 0.4960 1.0000
6.000 0.9114 0.02993 0.01822 -0.0563 0.4848 1.0000
6.250 0.9374 0.03032 0.01857 -0.0559 0.4759 1.0000
6.500 0.9561 0.03101 0.01931 -0.0547 0.4660 1.0000
6.750 0.9790 0.03157 0.01987 -0.0540 0.4576 1.0000
7.000 0.9988 0.03225 0.02059 -0.0530 0.4488 1.0000
7.250 1.0200 0.03289 0.02126 -0.0521 0.4406 1.0000
7.500 1.0391 0.03360 0.02201 -0.0510 0.4320 1.0000
7.750 1.0591 0.03428 0.02273 -0.0500 0.4239 1.0000
8.000 1.0770 0.03501 0.02350 -0.0487 0.4153 1.0000
8.250 1.0951 0.03575 0.02430 -0.0475 0.4071 1.0000
8.500 1.1124 0.03648 0.02508 -0.0461 0.3984 1.0000
8.750 1.1277 0.03731 0.02596 -0.0446 0.3900 1.0000
9.000 1.1447 0.03798 0.02667 -0.0432 0.3811 1.0000
9.250 1.1547 0.03896 0.02774 -0.0410 0.3724 1.0000
9.500 1.1740 0.03948 0.02827 -0.0398 0.3633 1.0000
9.750 1.1774 0.04080 0.02970 -0.0371 0.3544 1.0000
10.000 1.2009 0.04112 0.02998 -0.0364 0.3451 1.0000
10.250 1.1966 0.04291 0.03197 -0.0333 0.3364 1.0000
10.500 1.2228 0.04308 0.03207 -0.0327 0.3273 1.0000
10.750 1.2109 0.04542 0.03465 -0.0294 0.3187 1.0000
11.000 1.2372 0.04553 0.03469 -0.0288 0.3098 1.0000
11.250 1.2189 0.04851 0.03793 -0.0256 0.3014 1.0000
11.500 1.2432 0.04865 0.03804 -0.0248 0.2926 1.0000
11.750 1.2186 0.05244 0.04210 -0.0221 0.2842 1.0000
12.000 1.2415 0.05252 0.04215 -0.0212 0.2756 1.0000
12.250 1.2081 0.05761 0.04753 -0.0191 0.2673 1.0000
12.500 1.2323 0.05744 0.04732 -0.0181 0.2592 1.0000
12.750 1.1871 0.06452 0.05470 -0.0173 0.2507 1.0000
13.000 1.2136 0.06388 0.05400 -0.0162 0.2431 1.0000
13.250 1.1525 0.07401 0.06443 -0.0172 0.2341 1.0000
13.500 1.1874 0.07203 0.06240 -0.0156 0.2277 1.0000
13.750 1.1065 0.08648 0.07712 -0.0194 0.2175 1.0000
14.000 1.1558 0.08195 0.07256 -0.0166 0.2133 1.0000
14.250 1.0632 0.10021 0.09099 -0.0231 0.2016 1.0000
14.500 1.1096 0.09541 0.08622 -0.0200 0.1989 1.0000
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Polar data table (+)
Polar graphs
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