CLARK YM-15 AIRFOIL (clarym15-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: CLARK YM-15 AIRFOIL (clarym15-il) Reynolds number: 100,000 Max Cl/Cd: 48.7 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-clarym15-il-100000-n5.txt Download as CSV file: xf-clarym15-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.5093 0.07339 0.06781 -0.0684 1.0000 0.0528
-10.750 -0.5701 0.06415 0.05854 -0.0730 1.0000 0.0523
-10.500 -0.6172 0.06074 0.05511 -0.0703 1.0000 0.0521
-10.250 -0.6593 0.05843 0.05275 -0.0652 0.9995 0.0519
-10.000 -0.6731 0.05107 0.04481 -0.0698 0.9883 0.0521
-9.750 -0.6721 0.04587 0.03899 -0.0720 0.9800 0.0525
-9.500 -0.6582 0.04270 0.03546 -0.0731 0.9729 0.0531
-9.250 -0.6327 0.04106 0.03373 -0.0746 0.9682 0.0540
-9.000 -0.6118 0.03946 0.03197 -0.0750 0.9612 0.0550
-8.750 -0.5855 0.03753 0.02977 -0.0766 0.9567 0.0563
-8.500 -0.5662 0.03567 0.02762 -0.0765 0.9494 0.0574
-8.250 -0.5406 0.03368 0.02528 -0.0773 0.9441 0.0585
-8.000 -0.5096 0.03179 0.02300 -0.0789 0.9406 0.0598
-7.750 -0.4892 0.03060 0.02169 -0.0782 0.9325 0.0608
-7.500 -0.4580 0.02957 0.02062 -0.0794 0.9279 0.0622
-7.250 -0.4241 0.02857 0.01951 -0.0811 0.9247 0.0644
-7.000 -0.4029 0.02773 0.01850 -0.0802 0.9162 0.0666
-6.750 -0.3722 0.02669 0.01729 -0.0809 0.9114 0.0690
-6.500 -0.3387 0.02579 0.01641 -0.0823 0.9079 0.0714
-6.250 -0.3179 0.02515 0.01572 -0.0812 0.8991 0.0740
-6.000 -0.2870 0.02434 0.01475 -0.0818 0.8942 0.0779
-5.750 -0.2554 0.02358 0.01405 -0.0828 0.8901 0.0824
-5.500 -0.2340 0.02310 0.01348 -0.0816 0.8813 0.0880
-5.250 -0.2039 0.02239 0.01280 -0.0822 0.8765 0.0945
-5.000 -0.1771 0.02185 0.01220 -0.0820 0.8703 0.1024
-4.750 -0.1521 0.02135 0.01172 -0.0816 0.8631 0.1113
-4.500 -0.1212 0.02077 0.01117 -0.0822 0.8585 0.1228
-4.250 -0.0976 0.02041 0.01084 -0.0814 0.8508 0.1351
-4.000 -0.0700 0.01999 0.01049 -0.0814 0.8446 0.1520
-3.750 -0.0382 0.01953 0.01009 -0.0821 0.8403 0.1759
-3.500 -0.0167 0.01928 0.00997 -0.0810 0.8314 0.1995
-3.250 0.0125 0.01892 0.00967 -0.0811 0.8258 0.2289
-3.000 0.0402 0.01861 0.00944 -0.0810 0.8197 0.2589
-2.750 0.0650 0.01838 0.00926 -0.0804 0.8114 0.2867
-2.500 0.0966 0.01798 0.00890 -0.0807 0.8059 0.3180
-2.250 0.1190 0.01777 0.00879 -0.0796 0.7955 0.3468
-2.000 0.1498 0.01733 0.00843 -0.0797 0.7885 0.3841
-1.750 0.1722 0.01708 0.00833 -0.0785 0.7772 0.4256
-1.500 0.2007 0.01664 0.00806 -0.0782 0.7690 0.4844
-1.250 0.2232 0.01626 0.00800 -0.0767 0.7577 0.5648
-1.000 0.2467 0.01585 0.00800 -0.0750 0.7479 0.6759
-0.750 0.2746 0.01563 0.00805 -0.0737 0.7387 0.7811
-0.500 0.3083 0.01563 0.00811 -0.0739 0.7297 0.8493
-0.250 0.3482 0.01563 0.00805 -0.0755 0.7210 0.8934
0.000 0.3869 0.01570 0.00804 -0.0773 0.7113 0.9264
0.250 0.4282 0.01569 0.00790 -0.0795 0.7023 0.9522
0.500 0.4722 0.01575 0.00786 -0.0827 0.6907 0.9720
0.750 0.5196 0.01572 0.00771 -0.0866 0.6798 0.9879
1.000 0.5640 0.01570 0.00757 -0.0900 0.6683 1.0000
1.250 0.5833 0.01578 0.00758 -0.0884 0.6565 1.0000
1.500 0.6044 0.01583 0.00752 -0.0871 0.6453 1.0000
1.750 0.6258 0.01589 0.00748 -0.0858 0.6334 1.0000
2.000 0.6453 0.01600 0.00752 -0.0842 0.6200 1.0000
2.250 0.6657 0.01611 0.00754 -0.0828 0.6068 1.0000
2.500 0.6866 0.01623 0.00757 -0.0813 0.5935 1.0000
2.750 0.7079 0.01636 0.00758 -0.0800 0.5804 1.0000
3.000 0.7279 0.01652 0.00768 -0.0784 0.5663 1.0000
3.250 0.7479 0.01671 0.00779 -0.0769 0.5516 1.0000
3.500 0.7681 0.01691 0.00790 -0.0754 0.5366 1.0000
3.750 0.7883 0.01714 0.00804 -0.0739 0.5213 1.0000
4.000 0.8086 0.01739 0.00819 -0.0724 0.5062 1.0000
4.250 0.8291 0.01766 0.00837 -0.0710 0.4918 1.0000
4.750 0.8702 0.01826 0.00882 -0.0683 0.4645 1.0000
5.000 0.8907 0.01860 0.00909 -0.0670 0.4517 1.0000
5.250 0.9117 0.01895 0.00937 -0.0658 0.4402 1.0000
5.500 0.9329 0.01931 0.00967 -0.0647 0.4298 1.0000
5.750 0.9541 0.01969 0.01002 -0.0636 0.4200 1.0000
6.000 0.9758 0.02009 0.01033 -0.0626 0.4116 1.0000
6.250 0.9969 0.02049 0.01075 -0.0615 0.4026 1.0000
6.500 1.0188 0.02092 0.01109 -0.0606 0.3951 1.0000
6.750 1.0395 0.02135 0.01155 -0.0595 0.3867 1.0000
7.000 1.0608 0.02180 0.01194 -0.0585 0.3792 1.0000
7.250 1.0810 0.02226 0.01243 -0.0574 0.3712 1.0000
7.500 1.1013 0.02273 0.01286 -0.0563 0.3634 1.0000
7.750 1.1202 0.02322 0.01338 -0.0550 0.3550 1.0000
8.000 1.1386 0.02372 0.01384 -0.0536 0.3465 1.0000
8.250 1.1562 0.02423 0.01439 -0.0521 0.3381 1.0000
8.500 1.1734 0.02475 0.01492 -0.0506 0.3303 1.0000
8.750 1.1907 0.02529 0.01548 -0.0491 0.3233 1.0000
9.000 1.2060 0.02584 0.01611 -0.0474 0.3162 1.0000
9.250 1.2242 0.02641 0.01663 -0.0461 0.3098 1.0000
9.500 1.2373 0.02703 0.01740 -0.0441 0.3027 1.0000
9.750 1.2517 0.02765 0.01808 -0.0424 0.2957 1.0000
10.000 1.2657 0.02832 0.01881 -0.0407 0.2889 1.0000
10.250 1.2772 0.02905 0.01965 -0.0387 0.2813 1.0000
10.500 1.2898 0.02978 0.02039 -0.0370 0.2744 1.0000
10.750 1.2991 0.03064 0.02144 -0.0350 0.2661 1.0000
11.000 1.3092 0.03149 0.02229 -0.0331 0.2589 1.0000
11.250 1.3169 0.03252 0.02351 -0.0312 0.2497 1.0000
11.500 1.3242 0.03359 0.02462 -0.0293 0.2415 1.0000
11.750 1.3304 0.03481 0.02598 -0.0276 0.2319 1.0000
12.000 1.3360 0.03614 0.02739 -0.0259 0.2226 1.0000
12.250 1.3398 0.03762 0.02891 -0.0242 0.2137 1.0000
12.500 1.3435 0.03926 0.03065 -0.0228 0.2037 1.0000
12.750 1.3456 0.04107 0.03250 -0.0213 0.1949 1.0000
13.000 1.3464 0.04307 0.03452 -0.0200 0.1864 1.0000
13.250 1.3472 0.04519 0.03670 -0.0189 0.1786 1.0000
13.500 1.3464 0.04750 0.03902 -0.0178 0.1719 1.0000
13.750 1.3466 0.04985 0.04144 -0.0169 0.1657 1.0000
14.000 1.3458 0.05235 0.04400 -0.0161 0.1602 1.0000
14.250 1.3447 0.05492 0.04656 -0.0154 0.1556 1.0000
14.500 1.3449 0.05756 0.04934 -0.0149 0.1507 1.0000
14.750 1.3438 0.06032 0.05218 -0.0146 0.1464 1.0000
15.000 1.3443 0.06288 0.05471 -0.0141 0.1428 1.0000
15.250 1.3438 0.06581 0.05779 -0.0140 0.1390 1.0000
15.500 1.3426 0.06884 0.06094 -0.0140 0.1353 1.0000
15.750 1.3420 0.07177 0.06394 -0.0141 0.1320 1.0000
16.000 1.3457 0.07405 0.06616 -0.0138 0.1289 1.0000
16.250 1.3408 0.07784 0.07017 -0.0144 0.1258 1.0000
16.500 1.3363 0.08157 0.07406 -0.0150 0.1225 1.0000
16.750 1.3330 0.08511 0.07767 -0.0157 0.1193 1.0000
17.000 1.3367 0.08748 0.07998 -0.0158 0.1160 1.0000
17.250 1.3264 0.09236 0.08509 -0.0173 0.1134 1.0000
17.500 1.3176 0.09706 0.08997 -0.0188 0.1105 1.0000
17.750 1.3120 0.10126 0.09427 -0.0201 0.1077 1.0000
18.000 1.3118 0.10449 0.09753 -0.0211 0.1050 1.0000
18.250 1.3090 0.10824 0.10135 -0.0223 0.1025 1.0000
18.500 1.2940 0.11437 0.10772 -0.0250 0.1002 1.0000
18.750 1.2813 0.12019 0.11371 -0.0277 0.0978 1.0000
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Polar data table (+)
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