S4053 (s4053-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: S4053 (s4053-il) Reynolds number: 100,000 Max Cl/Cd: 58.91 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s4053-il-100000.txt Download as CSV file: xf-s4053-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: S4053
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3806 0.09396 0.08913 -0.0313 1.0000 0.0919
-8.000 -0.3883 0.09159 0.08686 -0.0328 1.0000 0.0949
-7.750 -0.4108 0.08999 0.08542 -0.0355 1.0000 0.0964
-7.500 -0.4294 0.08746 0.08294 -0.0424 1.0000 0.0971
-7.250 -0.4069 0.08276 0.07832 -0.0336 1.0000 0.1001
-7.000 -0.4033 0.08014 0.07575 -0.0320 1.0000 0.1034
-6.750 -0.4087 0.07736 0.07305 -0.0331 1.0000 0.1074
-6.500 -0.4355 0.07535 0.07085 -0.0418 1.0000 0.1113
-6.250 -0.4255 0.07096 0.06672 -0.0361 1.0000 0.1132
-6.000 -0.4232 0.06883 0.06466 -0.0324 1.0000 0.1163
-5.750 -0.4261 0.06655 0.06239 -0.0315 1.0000 0.1211
-5.500 -0.4319 0.06308 0.05879 -0.0338 1.0000 0.1274
-5.250 -0.4288 0.06096 0.05676 -0.0306 1.0000 0.1306
-5.000 -0.4259 0.05791 0.05349 -0.0329 1.0000 0.1414
-4.750 -0.4202 0.05564 0.05131 -0.0300 1.0000 0.1452
-4.500 -0.4118 0.05279 0.04831 -0.0308 1.0000 0.1573
-4.250 -0.3999 0.05028 0.04567 -0.0312 0.9997 0.1710
-4.000 -0.3679 0.04733 0.04273 -0.0336 0.9941 0.1914
-3.750 -0.3365 0.04461 0.03989 -0.0368 0.9873 0.2293
-3.500 -0.2620 0.03191 0.02485 -0.0456 0.9850 0.0792
-3.250 -0.2226 0.02859 0.02066 -0.0468 0.9796 0.0674
-3.000 -0.1840 0.02611 0.01774 -0.0487 0.9743 0.0647
-2.750 -0.1447 0.02433 0.01555 -0.0505 0.9691 0.0635
-2.500 -0.1084 0.02302 0.01400 -0.0518 0.9623 0.0658
-2.250 -0.0666 0.02183 0.01271 -0.0544 0.9577 0.0722
-2.000 -0.0364 0.02092 0.01184 -0.0548 0.9494 0.0790
-1.750 0.0042 0.01994 0.01088 -0.0571 0.9442 0.0985
-1.500 0.0601 0.01617 0.01035 -0.0614 0.9448 1.0000
-1.250 0.0926 0.01635 0.01016 -0.0626 0.9354 1.0000
-1.000 0.1394 0.01650 0.00997 -0.0665 0.9300 1.0000
-0.750 0.1684 0.01669 0.00993 -0.0671 0.9199 1.0000
-0.500 0.2080 0.01683 0.00987 -0.0696 0.9129 1.0000
-0.250 0.2446 0.01696 0.00981 -0.0715 0.9047 1.0000
0.000 0.2804 0.01709 0.00981 -0.0732 0.8967 1.0000
0.250 0.3227 0.01711 0.00971 -0.0760 0.8899 1.0000
0.500 0.3550 0.01725 0.00975 -0.0769 0.8810 1.0000
0.750 0.3973 0.01719 0.00961 -0.0795 0.8746 1.0000
1.000 0.4253 0.01737 0.00974 -0.0795 0.8646 1.0000
1.250 0.4693 0.01718 0.00951 -0.0822 0.8588 1.0000
1.500 0.4944 0.01738 0.00967 -0.0815 0.8475 1.0000
1.750 0.5234 0.01748 0.00976 -0.0815 0.8373 1.0000
2.000 0.5624 0.01726 0.00955 -0.0829 0.8300 1.0000
2.250 0.5872 0.01741 0.00970 -0.0820 0.8179 1.0000
2.500 0.6135 0.01751 0.00982 -0.0813 0.8063 1.0000
2.750 0.6419 0.01753 0.00988 -0.0808 0.7953 1.0000
3.000 0.6731 0.01741 0.00977 -0.0806 0.7849 1.0000
3.250 0.7012 0.01736 0.00974 -0.0799 0.7727 1.0000
3.500 0.7266 0.01738 0.00980 -0.0788 0.7590 1.0000
3.750 0.7525 0.01736 0.00984 -0.0776 0.7449 1.0000
4.000 0.7787 0.01731 0.00983 -0.0765 0.7303 1.0000
4.250 0.8051 0.01722 0.00978 -0.0754 0.7150 1.0000
4.500 0.8289 0.01721 0.00982 -0.0739 0.6974 1.0000
4.750 0.8527 0.01714 0.00984 -0.0723 0.6780 1.0000
5.000 0.8788 0.01694 0.00966 -0.0709 0.6584 1.0000
5.250 0.9013 0.01687 0.00966 -0.0692 0.6353 1.0000
5.500 0.9249 0.01673 0.00955 -0.0675 0.6106 1.0000
5.750 0.9466 0.01665 0.00954 -0.0656 0.5817 1.0000
6.000 0.9670 0.01664 0.00954 -0.0635 0.5475 1.0000
6.250 0.9862 0.01674 0.00960 -0.0612 0.5065 1.0000
6.500 1.0033 0.01704 0.00975 -0.0587 0.4574 1.0000
6.750 1.0172 0.01765 0.01013 -0.0560 0.3969 1.0000
7.000 1.0279 0.01865 0.01078 -0.0530 0.3310 1.0000
7.250 1.0366 0.01996 0.01169 -0.0499 0.2672 1.0000
7.500 1.0450 0.02151 0.01281 -0.0470 0.2168 1.0000
7.750 1.0561 0.02306 0.01410 -0.0445 0.1794 1.0000
8.000 1.0692 0.02457 0.01543 -0.0424 0.1530 1.0000
8.250 1.0851 0.02619 0.01685 -0.0407 0.1346 1.0000
8.500 1.1043 0.02789 0.01850 -0.0395 0.1196 1.0000
8.750 1.1247 0.02964 0.02019 -0.0386 0.1066 1.0000
9.000 1.1438 0.03118 0.02186 -0.0374 0.0959 1.0000
9.250 1.1621 0.03299 0.02385 -0.0361 0.0858 1.0000
9.500 1.1809 0.03516 0.02614 -0.0350 0.0765 1.0000
9.750 1.2021 0.03793 0.02889 -0.0346 0.0683 1.0000
10.000 1.2129 0.03973 0.03114 -0.0321 0.0622 1.0000
10.250 1.2327 0.04311 0.03455 -0.0317 0.0574 1.0000
10.500 1.2367 0.04612 0.03810 -0.0287 0.0546 1.0000
10.750 1.2385 0.04882 0.04125 -0.0258 0.0517 1.0000
11.000 1.2422 0.05155 0.04425 -0.0234 0.0492 1.0000
11.250 1.2432 0.05483 0.04781 -0.0211 0.0481 1.0000
11.500 1.2375 0.05821 0.05145 -0.0182 0.0474 1.0000
11.750 1.2259 0.06169 0.05522 -0.0151 0.0471 1.0000
12.000 1.2094 0.06531 0.05912 -0.0123 0.0471 1.0000
12.250 1.1865 0.06932 0.06346 -0.0102 0.0475 1.0000
12.500 1.1480 0.07463 0.06916 -0.0096 0.0486 1.0000
12.750 1.1126 0.08105 0.07588 -0.0111 0.0498 1.0000
13.000 1.0790 0.08842 0.08348 -0.0144 0.0510 1.0000
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Polar data table (+)
Polar graphs
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