S4062-095-87 (s4062-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: S4062-095-87 (s4062-il) Reynolds number: 1,000,000 Max Cl/Cd: 130.99 at α=2.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s4062-il-1000000-n5.txt Download as CSV file: xf-s4062-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S4062-095-87
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.2963 0.09152 0.08946 -0.0557 0.8825 0.0040
-9.750 -0.2964 0.08730 0.08522 -0.0574 0.8742 0.0039
-9.250 -0.5090 0.03268 0.03020 -0.0922 0.8367 0.0040
-9.000 -0.5036 0.02663 0.02365 -0.0953 0.8305 0.0040
-8.750 -0.4883 0.02328 0.01990 -0.0964 0.8258 0.0041
-8.500 -0.4684 0.02095 0.01726 -0.0970 0.8209 0.0041
-8.250 -0.4458 0.01939 0.01544 -0.0972 0.8164 0.0042
-8.000 -0.4222 0.01802 0.01382 -0.0973 0.8124 0.0042
-7.750 -0.3974 0.01686 0.01247 -0.0975 0.8082 0.0043
-7.500 -0.3721 0.01582 0.01123 -0.0976 0.8038 0.0043
-7.250 -0.3463 0.01497 0.01020 -0.0976 0.7997 0.0043
-7.000 -0.3213 0.01359 0.00858 -0.0977 0.7959 0.0045
-6.750 -0.2950 0.01273 0.00758 -0.0977 0.7916 0.0047
-6.500 -0.2680 0.01219 0.00693 -0.0978 0.7875 0.0049
-6.250 -0.2408 0.01170 0.00635 -0.0978 0.7837 0.0051
-6.000 -0.2132 0.01121 0.00578 -0.0979 0.7798 0.0053
-5.750 -0.1857 0.01074 0.00521 -0.0980 0.7755 0.0054
-5.500 -0.1580 0.01032 0.00470 -0.0980 0.7715 0.0056
-5.250 -0.1301 0.00994 0.00424 -0.0980 0.7677 0.0060
-5.000 -0.1020 0.00960 0.00384 -0.0981 0.7636 0.0062
-4.750 -0.0739 0.00932 0.00349 -0.0982 0.7594 0.0065
-4.500 -0.0458 0.00909 0.00318 -0.0982 0.7555 0.0067
-4.250 -0.0176 0.00873 0.00276 -0.0983 0.7516 0.0073
-4.000 0.0107 0.00849 0.00248 -0.0984 0.7473 0.0079
-3.750 0.0390 0.00830 0.00225 -0.0985 0.7432 0.0086
-3.500 0.0673 0.00814 0.00204 -0.0985 0.7393 0.0096
-3.250 0.0958 0.00794 0.00184 -0.0986 0.7351 0.0126
-3.000 0.1241 0.00773 0.00166 -0.0987 0.7308 0.0222
-2.750 0.1524 0.00755 0.00150 -0.0988 0.7266 0.0357
-2.500 0.1809 0.00740 0.00139 -0.0990 0.7226 0.0492
-2.250 0.2093 0.00723 0.00129 -0.0991 0.7182 0.0693
-2.000 0.2376 0.00710 0.00120 -0.0992 0.7138 0.0903
-1.500 0.2944 0.00683 0.00107 -0.0995 0.7049 0.1434
-1.250 0.3228 0.00674 0.00102 -0.0996 0.6998 0.1651
-1.000 0.3512 0.00666 0.00098 -0.0998 0.6949 0.1901
-0.750 0.3796 0.00656 0.00095 -0.0999 0.6885 0.2183
-0.500 0.4077 0.00650 0.00093 -0.1000 0.6806 0.2481
-0.250 0.4359 0.00643 0.00091 -0.1001 0.6707 0.2818
0.000 0.4639 0.00635 0.00091 -0.1002 0.6606 0.3209
0.250 0.4918 0.00628 0.00091 -0.1002 0.6504 0.3678
0.500 0.5198 0.00621 0.00093 -0.1003 0.6406 0.4161
0.750 0.5477 0.00611 0.00096 -0.1004 0.6316 0.4715
1.000 0.5754 0.00604 0.00100 -0.1005 0.6222 0.5308
1.250 0.6029 0.00595 0.00106 -0.1005 0.6111 0.5982
1.500 0.6301 0.00584 0.00112 -0.1004 0.5997 0.6766
1.750 0.6563 0.00569 0.00120 -0.1001 0.5878 0.7724
2.000 0.6789 0.00551 0.00129 -0.0988 0.5749 0.8861
2.250 0.7112 0.00548 0.00133 -0.0997 0.5583 1.0000
2.500 0.7382 0.00564 0.00141 -0.0996 0.5393 1.0000
2.750 0.7650 0.00584 0.00151 -0.0994 0.5166 1.0000
3.000 0.7910 0.00610 0.00164 -0.0992 0.4861 1.0000
3.250 0.8164 0.00644 0.00181 -0.0988 0.4502 1.0000
3.500 0.8416 0.00678 0.00199 -0.0985 0.4147 1.0000
3.750 0.8663 0.00717 0.00220 -0.0981 0.3779 1.0000
4.000 0.8913 0.00752 0.00242 -0.0977 0.3465 1.0000
4.250 0.9161 0.00788 0.00264 -0.0974 0.3164 1.0000
4.500 0.9411 0.00821 0.00285 -0.0970 0.2914 1.0000
4.750 0.9659 0.00855 0.00309 -0.0966 0.2656 1.0000
5.000 0.9899 0.00895 0.00334 -0.0961 0.2369 1.0000
5.250 1.0138 0.00935 0.00361 -0.0956 0.2102 1.0000
5.500 1.0385 0.00966 0.00385 -0.0952 0.1937 1.0000
5.750 1.0626 0.01001 0.00412 -0.0947 0.1758 1.0000
6.000 1.0855 0.01045 0.00444 -0.0941 0.1507 1.0000
6.250 1.1087 0.01086 0.00474 -0.0935 0.1312 1.0000
6.500 1.1318 0.01125 0.00506 -0.0929 0.1152 1.0000
6.750 1.1548 0.01163 0.00539 -0.0922 0.1015 1.0000
7.000 1.1766 0.01210 0.00577 -0.0914 0.0850 1.0000
7.250 1.1983 0.01256 0.00615 -0.0906 0.0712 1.0000
7.500 1.2195 0.01303 0.00655 -0.0896 0.0581 1.0000
7.750 1.2405 0.01350 0.00697 -0.0887 0.0478 1.0000
8.250 1.2813 0.01444 0.00785 -0.0866 0.0326 1.0000
8.500 1.3012 0.01491 0.00831 -0.0855 0.0267 1.0000
8.750 1.3191 0.01548 0.00884 -0.0841 0.0193 1.0000
9.000 1.3350 0.01608 0.00941 -0.0824 0.0138 1.0000
9.250 1.3506 0.01659 0.00994 -0.0805 0.0117 1.0000
9.500 1.3657 0.01713 0.01050 -0.0786 0.0106 1.0000
9.750 1.3806 0.01770 0.01110 -0.0768 0.0096 1.0000
10.000 1.3959 0.01826 0.01171 -0.0751 0.0092 1.0000
10.250 1.4111 0.01885 0.01235 -0.0734 0.0089 1.0000
10.500 1.4260 0.01948 0.01304 -0.0718 0.0085 1.0000
10.750 1.4400 0.02019 0.01379 -0.0701 0.0081 1.0000
11.000 1.4537 0.02093 0.01459 -0.0685 0.0078 1.0000
11.250 1.4666 0.02175 0.01546 -0.0668 0.0075 1.0000
11.500 1.4781 0.02270 0.01647 -0.0651 0.0071 1.0000
11.750 1.4889 0.02373 0.01757 -0.0634 0.0068 1.0000
12.000 1.4994 0.02480 0.01871 -0.0617 0.0066 1.0000
12.250 1.5117 0.02573 0.01972 -0.0603 0.0064 1.0000
12.500 1.5234 0.02674 0.02079 -0.0589 0.0063 1.0000
12.750 1.5339 0.02788 0.02201 -0.0575 0.0061 1.0000
13.000 1.5441 0.02905 0.02325 -0.0562 0.0059 1.0000
13.250 1.5540 0.03028 0.02455 -0.0549 0.0056 1.0000
13.500 1.5633 0.03160 0.02593 -0.0536 0.0054 1.0000
13.750 1.5713 0.03304 0.02744 -0.0524 0.0053 1.0000
14.000 1.5780 0.03465 0.02913 -0.0512 0.0051 1.0000
14.250 1.5838 0.03639 0.03095 -0.0501 0.0050 1.0000
14.500 1.5884 0.03828 0.03293 -0.0490 0.0048 1.0000
14.750 1.5901 0.04055 0.03530 -0.0479 0.0047 1.0000
15.000 1.5893 0.04315 0.03801 -0.0470 0.0045 1.0000
15.250 1.5938 0.04527 0.04022 -0.0464 0.0044 1.0000
15.500 1.5985 0.04743 0.04247 -0.0459 0.0043 1.0000
15.750 1.6027 0.04973 0.04486 -0.0455 0.0042 1.0000
16.000 1.6026 0.05262 0.04787 -0.0453 0.0041 1.0000
16.250 1.6064 0.05511 0.05044 -0.0453 0.0040 1.0000
16.500 1.6052 0.05835 0.05379 -0.0454 0.0039 1.0000
16.750 1.6047 0.06161 0.05715 -0.0457 0.0038 1.0000
17.000 1.6032 0.06513 0.06078 -0.0463 0.0037 1.0000
17.250 1.6017 0.06872 0.06447 -0.0470 0.0035 1.0000
17.500 1.5966 0.07302 0.06889 -0.0481 0.0035 1.0000
17.750 1.5906 0.07760 0.07358 -0.0495 0.0034 1.0000
18.000 1.5849 0.08231 0.07841 -0.0511 0.0033 1.0000
18.250 1.5750 0.08786 0.08408 -0.0532 0.0032 1.0000
18.500 1.5650 0.09365 0.08999 -0.0556 0.0031 1.0000
18.750 1.5504 0.10050 0.09699 -0.0587 0.0031 1.0000
19.000 1.5350 0.10769 0.10432 -0.0622 0.0031 1.0000
19.250 1.5183 0.11533 0.11210 -0.0661 0.0031 1.0000
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Polar data table (+)
Polar graphs
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