CLARK V AIRFOIL (clarkv-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: CLARK V AIRFOIL (clarkv-il) Reynolds number: 50,000 Max Cl/Cd: 36.45 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-clarkv-il-50000-n5.txt Download as CSV file: xf-clarkv-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: CLARK V 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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.4174 0.10477 0.09755 -0.0425 1.0000 0.0745
-9.250 -0.4256 0.10145 0.09431 -0.0424 1.0000 0.0745
-9.000 -0.4359 0.09815 0.09111 -0.0422 1.0000 0.0745
-8.750 -0.4485 0.09489 0.08795 -0.0417 1.0000 0.0743
-8.500 -0.4644 0.09171 0.08487 -0.0409 1.0000 0.0740
-8.250 -0.4833 0.08840 0.08168 -0.0402 1.0000 0.0734
-8.000 -0.4993 0.08414 0.07749 -0.0410 1.0000 0.0728
-7.750 -0.5141 0.07944 0.07281 -0.0418 1.0000 0.0722
-7.500 -0.5273 0.07449 0.06783 -0.0426 1.0000 0.0716
-7.250 -0.5380 0.06933 0.06255 -0.0433 1.0000 0.0709
-7.000 -0.5444 0.06423 0.05724 -0.0438 1.0000 0.0705
-6.750 -0.5449 0.05956 0.05230 -0.0441 1.0000 0.0705
-6.500 -0.5399 0.05576 0.04821 -0.0440 1.0000 0.0716
-6.250 -0.5314 0.05222 0.04432 -0.0439 1.0000 0.0736
-6.000 -0.5199 0.04860 0.04023 -0.0439 1.0000 0.0755
-5.750 -0.5047 0.04518 0.03629 -0.0439 1.0000 0.0765
-5.500 -0.4864 0.04217 0.03270 -0.0438 1.0000 0.0775
-5.250 -0.4658 0.03963 0.02956 -0.0437 1.0000 0.0788
-5.000 -0.4414 0.03774 0.02744 -0.0442 0.9986 0.0818
-4.750 -0.4085 0.03630 0.02577 -0.0462 0.9947 0.0857
-4.500 -0.3754 0.03465 0.02373 -0.0478 0.9906 0.0886
-4.250 -0.3408 0.03321 0.02184 -0.0494 0.9866 0.0916
-4.000 -0.3074 0.03202 0.02039 -0.0507 0.9824 0.0953
-3.750 -0.2748 0.03125 0.01959 -0.0522 0.9776 0.1020
-3.500 -0.2400 0.03049 0.01861 -0.0538 0.9734 0.1098
-3.250 -0.2090 0.02979 0.01786 -0.0547 0.9679 0.1175
-3.000 -0.1738 0.02921 0.01720 -0.0564 0.9634 0.1303
-2.750 -0.1426 0.02867 0.01661 -0.0575 0.9576 0.1513
-2.500 -0.1090 0.02803 0.01613 -0.0592 0.9524 0.1865
-2.250 -0.0729 0.02724 0.01588 -0.0617 0.9483 0.2714
-2.000 -0.0469 0.02648 0.01578 -0.0619 0.9414 0.4136
-1.750 -0.0178 0.02584 0.01585 -0.0620 0.9362 0.5757
-1.500 0.0027 0.02531 0.01605 -0.0590 0.9300 0.7778
-1.250 0.0510 0.02526 0.01591 -0.0628 0.9231 1.0000
-1.000 0.0836 0.02551 0.01583 -0.0642 0.9162 1.0000
-0.750 0.1136 0.02575 0.01578 -0.0652 0.9082 1.0000
-0.500 0.1448 0.02600 0.01579 -0.0663 0.9009 1.0000
-0.250 0.1754 0.02625 0.01582 -0.0673 0.8930 1.0000
0.000 0.2041 0.02651 0.01590 -0.0679 0.8848 1.0000
0.250 0.2369 0.02674 0.01597 -0.0692 0.8775 1.0000
0.500 0.2627 0.02701 0.01611 -0.0692 0.8682 1.0000
0.750 0.2987 0.02720 0.01617 -0.0709 0.8618 1.0000
1.000 0.3222 0.02749 0.01638 -0.0705 0.8515 1.0000
1.250 0.3550 0.02768 0.01648 -0.0716 0.8440 1.0000
1.500 0.3833 0.02789 0.01663 -0.0719 0.8345 1.0000
1.750 0.4095 0.02813 0.01682 -0.0718 0.8243 1.0000
2.000 0.4474 0.02810 0.01675 -0.0734 0.8173 1.0000
2.250 0.4713 0.02830 0.01694 -0.0728 0.8052 1.0000
2.500 0.4986 0.02841 0.01704 -0.0726 0.7940 1.0000
2.750 0.5382 0.02812 0.01676 -0.0741 0.7868 1.0000
3.000 0.5617 0.02827 0.01694 -0.0732 0.7740 1.0000
3.500 0.6198 0.02822 0.01695 -0.0730 0.7522 1.0000
3.750 0.6525 0.02803 0.01684 -0.0733 0.7419 1.0000
4.000 0.6775 0.02809 0.01696 -0.0725 0.7288 1.0000
4.250 0.7046 0.02806 0.01701 -0.0719 0.7157 1.0000
4.500 0.7335 0.02793 0.01697 -0.0715 0.7025 1.0000
4.750 0.7634 0.02772 0.01685 -0.0712 0.6885 1.0000
5.000 0.7924 0.02750 0.01673 -0.0706 0.6729 1.0000
5.250 0.8209 0.02727 0.01659 -0.0699 0.6558 1.0000
5.500 0.8501 0.02701 0.01642 -0.0692 0.6376 1.0000
5.750 0.8808 0.02673 0.01622 -0.0688 0.6188 1.0000
6.000 0.9025 0.02687 0.01644 -0.0672 0.5969 1.0000
6.250 0.9290 0.02685 0.01648 -0.0663 0.5748 1.0000
6.500 0.9522 0.02702 0.01670 -0.0650 0.5512 1.0000
6.750 0.9771 0.02715 0.01687 -0.0639 0.5267 1.0000
7.000 0.9966 0.02754 0.01730 -0.0621 0.5004 1.0000
7.250 1.0167 0.02795 0.01770 -0.0605 0.4741 1.0000
7.500 1.0359 0.02842 0.01814 -0.0587 0.4477 1.0000
7.750 1.0516 0.02905 0.01877 -0.0566 0.4210 1.0000
8.000 1.0657 0.02979 0.01947 -0.0543 0.3948 1.0000
8.250 1.0800 0.03059 0.02019 -0.0521 0.3703 1.0000
8.500 1.0930 0.03151 0.02109 -0.0499 0.3471 1.0000
8.750 1.1075 0.03245 0.02198 -0.0480 0.3265 1.0000
9.000 1.1203 0.03351 0.02314 -0.0460 0.3065 1.0000
9.250 1.1333 0.03461 0.02429 -0.0440 0.2879 1.0000
9.500 1.1457 0.03575 0.02548 -0.0421 0.2704 1.0000
9.750 1.1567 0.03695 0.02673 -0.0400 0.2535 1.0000
10.000 1.1668 0.03822 0.02804 -0.0380 0.2374 1.0000
10.250 1.1747 0.03957 0.02943 -0.0358 0.2215 1.0000
10.500 1.1804 0.04105 0.03100 -0.0335 0.2059 1.0000
10.750 1.1832 0.04269 0.03272 -0.0311 0.1901 1.0000
11.000 1.1830 0.04452 0.03461 -0.0288 0.1743 1.0000
11.250 1.1808 0.04655 0.03671 -0.0266 0.1588 1.0000
11.500 1.1778 0.04880 0.03902 -0.0247 0.1436 1.0000
11.750 1.1748 0.05125 0.04154 -0.0231 0.1293 1.0000
12.000 1.1720 0.05388 0.04423 -0.0217 0.1166 1.0000
12.250 1.1682 0.05674 0.04711 -0.0205 0.1055 1.0000
12.500 1.1641 0.05982 0.05025 -0.0196 0.0954 1.0000
12.750 1.1606 0.06308 0.05365 -0.0187 0.0862 1.0000
13.000 1.1559 0.06649 0.05707 -0.0182 0.0794 1.0000
13.250 1.1523 0.07000 0.06072 -0.0177 0.0729 1.0000
13.500 1.1485 0.07350 0.06422 -0.0174 0.0685 1.0000
13.750 1.1457 0.07729 0.06830 -0.0172 0.0639 1.0000
14.000 1.1414 0.08108 0.07219 -0.0174 0.0605 1.0000
14.250 1.1380 0.08477 0.07587 -0.0176 0.0577 1.0000
14.500 1.1315 0.08949 0.08094 -0.0184 0.0552 1.0000
14.750 1.1240 0.09442 0.08612 -0.0195 0.0533 1.0000
15.000 1.1158 0.09955 0.09147 -0.0209 0.0519 1.0000
15.250 1.1068 0.10495 0.09705 -0.0228 0.0507 1.0000
15.500 1.0984 0.11036 0.10260 -0.0249 0.0496 1.0000
15.750 1.0947 0.11479 0.10708 -0.0264 0.0482 1.0000
16.000 1.0816 0.12164 0.11409 -0.0297 0.0476 1.0000
16.250 1.0614 0.13067 0.12336 -0.0348 0.0476 1.0000
16.500 1.0390 0.14104 0.13391 -0.0409 0.0477 1.0000
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