S4062-095-87 (s4062-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: S4062-095-87 (s4062-il) Reynolds number: 100,000 Max Cl/Cd: 62.73 at α=7° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s4062-il-100000.txt Download as CSV file: xf-s4062-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3811 0.10360 0.09936 -0.0301 1.0000 0.0888
-7.750 -0.4072 0.10366 0.09956 -0.0276 1.0000 0.0892
-7.500 -0.4308 0.10327 0.09927 -0.0259 1.0000 0.0894
-7.250 -0.4501 0.10193 0.09800 -0.0283 1.0000 0.0897
-7.000 -0.4423 0.09720 0.09331 -0.0224 1.0000 0.0911
-6.750 -0.4372 0.09460 0.09071 -0.0184 1.0000 0.0931
-6.500 -0.4419 0.09261 0.08876 -0.0168 1.0000 0.0948
-6.250 -0.4243 0.08845 0.08460 -0.0235 0.9947 0.1000
-6.000 -0.4055 0.08184 0.07792 -0.0392 0.9865 0.1051
-5.750 -0.3866 0.07883 0.07492 -0.0372 0.9834 0.1083
-5.250 -0.3429 0.06977 0.06574 -0.0503 0.9720 0.1220
-5.000 -0.3214 0.06501 0.06077 -0.0591 0.9649 0.1340
-4.750 -0.3016 0.06265 0.05847 -0.0575 0.9608 0.1409
-4.500 -0.2754 0.05836 0.05402 -0.0632 0.9557 0.1518
-4.250 -0.2190 0.04102 0.03522 -0.0793 0.9520 0.0717
-4.000 -0.1786 0.03455 0.02753 -0.0830 0.9488 0.0615
-3.750 -0.1396 0.03127 0.02355 -0.0856 0.9458 0.0613
-3.500 -0.1071 0.02905 0.02080 -0.0868 0.9419 0.0645
-3.250 -0.0799 0.02797 0.01960 -0.0871 0.9367 0.0713
-3.000 -0.0438 0.02639 0.01774 -0.0884 0.9330 0.0800
-2.750 -0.0052 0.02546 0.01670 -0.0904 0.9295 0.1056
-2.500 0.0155 0.02490 0.01625 -0.0895 0.9233 0.1371
-2.250 0.0487 0.02439 0.01587 -0.0909 0.9187 0.1872
-2.000 0.0848 0.02397 0.01566 -0.0927 0.9148 0.2468
-1.750 0.1036 0.02371 0.01560 -0.0915 0.9082 0.3007
-1.500 0.1363 0.02326 0.01559 -0.0927 0.9037 0.4000
-1.250 0.1655 0.02266 0.01578 -0.0928 0.8994 0.5880
-1.000 0.1918 0.02192 0.01581 -0.0917 0.8935 1.0000
-0.750 0.2288 0.02230 0.01584 -0.0937 0.8886 1.0000
-0.500 0.2532 0.02276 0.01606 -0.0936 0.8820 1.0000
-0.250 0.2831 0.02316 0.01625 -0.0943 0.8757 1.0000
0.000 0.3260 0.02351 0.01638 -0.0971 0.8718 1.0000
0.250 0.3385 0.02403 0.01679 -0.0950 0.8625 1.0000
0.500 0.3794 0.02433 0.01693 -0.0974 0.8579 1.0000
0.750 0.3954 0.02487 0.01738 -0.0959 0.8488 1.0000
1.000 0.4354 0.02512 0.01753 -0.0980 0.8437 1.0000
1.250 0.4536 0.02566 0.01800 -0.0967 0.8344 1.0000
1.500 0.4957 0.02577 0.01804 -0.0990 0.8290 1.0000
1.750 0.5148 0.02626 0.01848 -0.0978 0.8189 1.0000
2.000 0.5613 0.02616 0.01836 -0.1005 0.8140 1.0000
2.250 0.5794 0.02662 0.01880 -0.0991 0.8030 1.0000
2.500 0.6315 0.02620 0.01838 -0.1023 0.7988 1.0000
2.750 0.6511 0.02654 0.01873 -0.1009 0.7871 1.0000
3.000 0.6798 0.02661 0.01883 -0.1007 0.7775 1.0000
3.250 0.7232 0.02598 0.01824 -0.1020 0.7713 1.0000
3.500 0.7482 0.02606 0.01836 -0.1012 0.7604 1.0000
3.750 0.7942 0.02507 0.01745 -0.1024 0.7557 1.0000
4.000 0.8185 0.02504 0.01748 -0.1013 0.7439 1.0000
4.250 0.8488 0.02465 0.01717 -0.1007 0.7339 1.0000
4.500 0.8903 0.02354 0.01616 -0.1011 0.7272 1.0000
4.750 0.9179 0.02314 0.01586 -0.1001 0.7150 1.0000
5.000 0.9483 0.02252 0.01534 -0.0992 0.7032 1.0000
5.250 0.9811 0.02170 0.01461 -0.0985 0.6912 1.0000
5.500 1.0127 0.02090 0.01393 -0.0976 0.6773 1.0000
5.750 1.0421 0.02020 0.01333 -0.0965 0.6605 1.0000
6.000 1.0724 0.01944 0.01264 -0.0954 0.6415 1.0000
6.250 1.0976 0.01899 0.01230 -0.0939 0.6170 1.0000
6.500 1.1223 0.01861 0.01195 -0.0922 0.5872 1.0000
6.750 1.1453 0.01841 0.01170 -0.0903 0.5496 1.0000
7.000 1.1642 0.01856 0.01175 -0.0881 0.5025 1.0000
7.250 1.1807 0.01908 0.01198 -0.0856 0.4513 1.0000
7.500 1.1944 0.01995 0.01257 -0.0832 0.4026 1.0000
7.750 1.2072 0.02101 0.01335 -0.0808 0.3607 1.0000
8.000 1.2193 0.02213 0.01427 -0.0784 0.3239 1.0000
8.500 1.2426 0.02450 0.01632 -0.0739 0.2627 1.0000
8.750 1.2531 0.02574 0.01746 -0.0715 0.2353 1.0000
9.000 1.2617 0.02701 0.01866 -0.0690 0.2095 1.0000
9.250 1.2681 0.02835 0.01989 -0.0662 0.1863 1.0000
9.500 1.2725 0.02970 0.02116 -0.0633 0.1646 1.0000
9.750 1.2761 0.03116 0.02259 -0.0606 0.1439 1.0000
10.000 1.2798 0.03272 0.02412 -0.0581 0.1254 1.0000
10.250 1.2845 0.03455 0.02583 -0.0558 0.1091 1.0000
10.500 1.2904 0.03655 0.02781 -0.0537 0.0939 1.0000
10.750 1.2991 0.03876 0.03001 -0.0518 0.0807 1.0000
11.000 1.3119 0.04106 0.03220 -0.0504 0.0702 1.0000
11.250 1.3220 0.04309 0.03450 -0.0487 0.0633 1.0000
11.500 1.3500 0.04614 0.03756 -0.0485 0.0576 1.0000
11.750 1.3641 0.04878 0.04054 -0.0471 0.0542 1.0000
12.000 1.3727 0.05112 0.04306 -0.0456 0.0509 1.0000
12.250 1.3934 0.05537 0.04740 -0.0456 0.0479 1.0000
12.500 1.3900 0.05852 0.05095 -0.0432 0.0472 1.0000
12.750 1.3833 0.06208 0.05490 -0.0410 0.0467 1.0000
13.000 1.3728 0.06595 0.05915 -0.0391 0.0464 1.0000
13.250 1.3586 0.07017 0.06371 -0.0376 0.0462 1.0000
13.500 1.3420 0.07473 0.06859 -0.0366 0.0462 1.0000
13.750 1.3227 0.07974 0.07390 -0.0362 0.0463 1.0000
14.000 1.3016 0.08520 0.07963 -0.0366 0.0464 1.0000
14.250 1.2790 0.09117 0.08585 -0.0378 0.0466 1.0000
14.500 1.2553 0.09770 0.09260 -0.0399 0.0469 1.0000
14.750 1.2315 0.10479 0.09989 -0.0429 0.0472 1.0000
15.000 1.2075 0.11255 0.10782 -0.0468 0.0476 1.0000
15.250 1.1849 0.12098 0.11638 -0.0514 0.0480 1.0000
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Polar data table (+)
Polar graphs
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