CLARK YM-15 AIRFOIL (clarym15-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: CLARK YM-15 AIRFOIL (clarym15-il) Reynolds number: 200,000 Max Cl/Cd: 62.71 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-clarym15-il-200000-n5.txt Download as CSV file: xf-clarym15-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.750 -0.7302 0.05056 0.04563 -0.0895 1.0000 0.0364
-12.500 -0.7637 0.04666 0.04155 -0.0888 1.0000 0.0364
-12.250 -0.7963 0.04455 0.03933 -0.0843 1.0000 0.0364
-12.000 -0.8163 0.04277 0.03742 -0.0805 0.9976 0.0365
-11.750 -0.8027 0.04012 0.03455 -0.0824 0.9918 0.0368
-11.500 -0.7871 0.03780 0.03200 -0.0837 0.9857 0.0372
-11.250 -0.7672 0.03569 0.02966 -0.0853 0.9815 0.0377
-11.000 -0.7494 0.03389 0.02763 -0.0857 0.9750 0.0383
-10.750 -0.7258 0.03209 0.02557 -0.0870 0.9711 0.0390
-10.500 -0.7042 0.03049 0.02372 -0.0875 0.9657 0.0396
-10.250 -0.6806 0.02901 0.02198 -0.0880 0.9605 0.0401
-10.000 -0.6531 0.02762 0.02038 -0.0890 0.9570 0.0405
-9.750 -0.6297 0.02650 0.01922 -0.0890 0.9510 0.0410
-9.500 -0.6041 0.02553 0.01820 -0.0894 0.9456 0.0416
-9.250 -0.5749 0.02459 0.01718 -0.0903 0.9418 0.0422
-9.000 -0.5515 0.02378 0.01629 -0.0899 0.9351 0.0428
-8.750 -0.5255 0.02299 0.01541 -0.0900 0.9292 0.0437
-8.500 -0.4965 0.02217 0.01448 -0.0906 0.9250 0.0447
-8.250 -0.4738 0.02150 0.01370 -0.0898 0.9173 0.0457
-8.000 -0.4474 0.02076 0.01286 -0.0898 0.9113 0.0465
-7.750 -0.4204 0.02005 0.01214 -0.0899 0.9062 0.0475
-7.500 -0.3973 0.01950 0.01156 -0.0892 0.8980 0.0484
-7.250 -0.3699 0.01892 0.01092 -0.0892 0.8925 0.0497
-7.000 -0.3455 0.01841 0.01035 -0.0886 0.8851 0.0510
-6.750 -0.3197 0.01790 0.00976 -0.0883 0.8782 0.0526
-6.500 -0.2929 0.01739 0.00923 -0.0881 0.8725 0.0545
-6.250 -0.2686 0.01701 0.00884 -0.0875 0.8645 0.0570
-6.000 -0.2411 0.01660 0.00835 -0.0873 0.8585 0.0603
-5.750 -0.2162 0.01621 0.00798 -0.0868 0.8512 0.0638
-5.500 -0.1898 0.01588 0.00758 -0.0865 0.8442 0.0686
-5.250 -0.1628 0.01550 0.00720 -0.0863 0.8383 0.0742
-5.000 -0.1376 0.01521 0.00689 -0.0858 0.8305 0.0806
-4.750 -0.1100 0.01494 0.00656 -0.0856 0.8243 0.0884
-4.500 -0.0844 0.01465 0.00630 -0.0852 0.8169 0.0964
-4.250 -0.0578 0.01440 0.00602 -0.0849 0.8096 0.1049
-4.000 -0.0309 0.01415 0.00575 -0.0846 0.8023 0.1143
-3.750 -0.0052 0.01389 0.00551 -0.0841 0.7931 0.1251
-3.500 0.0213 0.01364 0.00527 -0.0838 0.7845 0.1399
-3.250 0.0470 0.01337 0.00510 -0.0833 0.7752 0.1650
-3.000 0.0730 0.01311 0.00496 -0.0830 0.7667 0.1995
-2.750 0.0990 0.01291 0.00483 -0.0825 0.7574 0.2305
-2.500 0.1254 0.01275 0.00470 -0.0822 0.7486 0.2551
-2.250 0.1518 0.01261 0.00456 -0.0817 0.7391 0.2780
-2.000 0.1779 0.01247 0.00445 -0.0813 0.7291 0.3004
-1.750 0.2043 0.01232 0.00432 -0.0809 0.7195 0.3235
-1.500 0.2298 0.01218 0.00424 -0.0803 0.7089 0.3496
-1.250 0.2558 0.01202 0.00414 -0.0799 0.6999 0.3832
-0.750 0.3054 0.01163 0.00406 -0.0785 0.6809 0.4848
-0.500 0.3282 0.01133 0.00406 -0.0774 0.6711 0.5704
-0.250 0.3498 0.01101 0.00414 -0.0758 0.6621 0.6795
0.000 0.3730 0.01085 0.00424 -0.0742 0.6525 0.7715
0.250 0.4000 0.01084 0.00434 -0.0734 0.6425 0.8322
0.500 0.4310 0.01091 0.00439 -0.0736 0.6318 0.8734
0.750 0.4633 0.01101 0.00446 -0.0741 0.6195 0.9047
1.000 0.4974 0.01112 0.00450 -0.0752 0.6070 0.9272
1.250 0.5320 0.01125 0.00454 -0.0764 0.5945 0.9458
1.500 0.5671 0.01139 0.00457 -0.0778 0.5815 0.9608
1.750 0.6029 0.01152 0.00463 -0.0794 0.5674 0.9736
2.000 0.6407 0.01168 0.00469 -0.0815 0.5526 0.9842
2.250 0.6802 0.01184 0.00475 -0.0841 0.5361 0.9937
2.500 0.7163 0.01202 0.00481 -0.0860 0.5186 1.0000
2.750 0.7356 0.01219 0.00489 -0.0843 0.5028 1.0000
3.000 0.7546 0.01238 0.00499 -0.0827 0.4872 1.0000
3.250 0.7734 0.01259 0.00510 -0.0810 0.4715 1.0000
3.500 0.7920 0.01282 0.00523 -0.0792 0.4556 1.0000
3.750 0.8104 0.01306 0.00538 -0.0774 0.4401 1.0000
4.000 0.8284 0.01332 0.00555 -0.0755 0.4250 1.0000
4.250 0.8464 0.01361 0.00573 -0.0737 0.4110 1.0000
4.500 0.8653 0.01389 0.00594 -0.0720 0.3983 1.0000
4.750 0.8848 0.01417 0.00616 -0.0705 0.3882 1.0000
5.000 0.9041 0.01448 0.00639 -0.0690 0.3794 1.0000
5.250 0.9247 0.01477 0.00665 -0.0677 0.3713 1.0000
5.500 0.9448 0.01510 0.00692 -0.0663 0.3639 1.0000
5.750 0.9657 0.01541 0.00720 -0.0652 0.3573 1.0000
6.000 0.9865 0.01573 0.00749 -0.0640 0.3501 1.0000
6.250 1.0062 0.01611 0.00780 -0.0627 0.3436 1.0000
6.500 1.0276 0.01641 0.00812 -0.0616 0.3365 1.0000
6.750 1.0466 0.01680 0.00845 -0.0602 0.3286 1.0000
7.000 1.0665 0.01713 0.00879 -0.0589 0.3206 1.0000
7.250 1.0848 0.01750 0.00914 -0.0574 0.3132 1.0000
7.500 1.1036 0.01789 0.00950 -0.0560 0.3079 1.0000
7.750 1.1239 0.01820 0.00988 -0.0548 0.3026 1.0000
8.000 1.1429 0.01858 0.01027 -0.0535 0.2973 1.0000
8.250 1.1606 0.01904 0.01069 -0.0520 0.2923 1.0000
8.500 1.1807 0.01937 0.01112 -0.0509 0.2867 1.0000
8.750 1.1993 0.01978 0.01157 -0.0496 0.2811 1.0000
9.000 1.2161 0.02028 0.01206 -0.0481 0.2758 1.0000
9.250 1.2352 0.02067 0.01255 -0.0470 0.2696 1.0000
9.500 1.2519 0.02116 0.01308 -0.0456 0.2629 1.0000
9.750 1.2683 0.02169 0.01365 -0.0442 0.2564 1.0000
10.000 1.2850 0.02221 0.01424 -0.0429 0.2489 1.0000
10.250 1.2996 0.02284 0.01489 -0.0414 0.2416 1.0000
10.500 1.3150 0.02346 0.01558 -0.0400 0.2323 1.0000
10.750 1.3285 0.02419 0.01635 -0.0385 0.2226 1.0000
11.000 1.3400 0.02506 0.01722 -0.0369 0.2117 1.0000
11.250 1.3508 0.02602 0.01819 -0.0353 0.1996 1.0000
11.500 1.3605 0.02710 0.01928 -0.0338 0.1877 1.0000
11.750 1.3686 0.02834 0.02050 -0.0321 0.1767 1.0000
12.000 1.3751 0.02973 0.02189 -0.0305 0.1668 1.0000
12.250 1.3801 0.03130 0.02344 -0.0289 0.1574 1.0000
12.500 1.3863 0.03284 0.02501 -0.0275 0.1488 1.0000
12.750 1.3893 0.03467 0.02684 -0.0261 0.1414 1.0000
13.000 1.3948 0.03638 0.02859 -0.0249 0.1342 1.0000
13.250 1.3964 0.03845 0.03067 -0.0237 0.1285 1.0000
13.500 1.4021 0.04023 0.03252 -0.0228 0.1232 1.0000
13.750 1.4041 0.04239 0.03471 -0.0218 0.1185 1.0000
14.000 1.4060 0.04464 0.03701 -0.0210 0.1147 1.0000
14.250 1.4104 0.04671 0.03918 -0.0204 0.1109 1.0000
14.500 1.4119 0.04913 0.04166 -0.0198 0.1073 1.0000
14.750 1.4106 0.05190 0.04447 -0.0194 0.1042 1.0000
15.000 1.4133 0.05434 0.04700 -0.0191 0.1014 1.0000
15.250 1.4156 0.05687 0.04964 -0.0189 0.0986 1.0000
15.500 1.4157 0.05970 0.05255 -0.0188 0.0960 1.0000
15.750 1.4137 0.06284 0.05576 -0.0188 0.0937 1.0000
16.000 1.4108 0.06615 0.05912 -0.0190 0.0916 1.0000
16.250 1.4127 0.06896 0.06207 -0.0192 0.0893 1.0000
16.500 1.4123 0.07208 0.06530 -0.0196 0.0871 1.0000
16.750 1.4100 0.07551 0.06882 -0.0200 0.0849 1.0000
17.000 1.4059 0.07921 0.07260 -0.0207 0.0831 1.0000
17.250 1.4002 0.08318 0.07662 -0.0215 0.0813 1.0000
17.500 1.3996 0.08654 0.08013 -0.0222 0.0793 1.0000
17.750 1.3969 0.09024 0.08396 -0.0231 0.0770 1.0000
18.000 1.3919 0.09431 0.08813 -0.0242 0.0747 1.0000
18.250 1.3855 0.09863 0.09252 -0.0255 0.0728 1.0000
18.500 1.3796 0.10292 0.09688 -0.0269 0.0710 1.0000
18.750 1.3769 0.10680 0.10091 -0.0282 0.0687 1.0000
19.000 1.3714 0.11115 0.10538 -0.0298 0.0662 1.0000
19.250 1.3639 0.11585 0.11016 -0.0316 0.0639 1.0000
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