S4061-096-84 (s4061-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: S4061-096-84 (s4061-il) Reynolds number: 500,000 Max Cl/Cd: 105.72 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s4061-il-500000-n5.txt Download as CSV file: xf-s4061-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S4061-096-84
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.3644 0.10586 0.10359 -0.0280 1.0000 0.0116
-9.750 -0.2708 0.08587 0.08357 -0.0348 0.8932 0.0082
-9.500 -0.3532 0.09378 0.09154 -0.0325 0.9858 0.0082
-9.000 -0.3250 0.08393 0.08164 -0.0437 0.9396 0.0079
-8.750 -0.3178 0.08021 0.07786 -0.0466 0.9191 0.0076
-8.250 -0.3239 0.07172 0.06928 -0.0504 0.8845 0.0074
-7.750 -0.4226 0.02721 0.02354 -0.0827 0.8447 0.0065
-7.500 -0.4049 0.02370 0.01951 -0.0836 0.8379 0.0065
-7.250 -0.3831 0.02141 0.01683 -0.0839 0.8309 0.0067
-7.000 -0.3597 0.01966 0.01475 -0.0840 0.8248 0.0069
-6.750 -0.3349 0.01818 0.01298 -0.0841 0.8183 0.0071
-6.500 -0.3096 0.01697 0.01150 -0.0840 0.8120 0.0073
-6.250 -0.2835 0.01591 0.01022 -0.0840 0.8060 0.0075
-6.000 -0.2571 0.01501 0.00911 -0.0839 0.7996 0.0078
-5.750 -0.2305 0.01426 0.00818 -0.0838 0.7939 0.0080
-5.500 -0.2033 0.01361 0.00739 -0.0837 0.7875 0.0082
-5.250 -0.1764 0.01295 0.00659 -0.0836 0.7815 0.0085
-5.000 -0.1493 0.01229 0.00585 -0.0836 0.7756 0.0092
-4.750 -0.1218 0.01183 0.00531 -0.0836 0.7691 0.0096
-4.500 -0.0943 0.01138 0.00476 -0.0835 0.7634 0.0101
-4.250 -0.0664 0.01097 0.00427 -0.0835 0.7569 0.0105
-4.000 -0.0385 0.01064 0.00382 -0.0834 0.7508 0.0111
-3.750 -0.0104 0.01031 0.00342 -0.0834 0.7445 0.0117
-3.500 0.0176 0.01001 0.00305 -0.0834 0.7380 0.0130
-3.250 0.0457 0.00978 0.00275 -0.0834 0.7319 0.0149
-3.000 0.0737 0.00948 0.00247 -0.0834 0.7252 0.0232
-2.750 0.1016 0.00920 0.00225 -0.0834 0.7190 0.0450
-2.500 0.1298 0.00900 0.00208 -0.0834 0.7122 0.0639
-2.250 0.1578 0.00882 0.00194 -0.0835 0.7057 0.0875
-2.000 0.1860 0.00862 0.00184 -0.0835 0.6989 0.1181
-1.750 0.2140 0.00845 0.00174 -0.0836 0.6921 0.1524
-1.500 0.2422 0.00833 0.00166 -0.0836 0.6855 0.1783
-1.250 0.2704 0.00821 0.00159 -0.0837 0.6782 0.2074
-1.000 0.2985 0.00809 0.00153 -0.0837 0.6715 0.2432
-0.750 0.3266 0.00796 0.00149 -0.0838 0.6641 0.2850
-0.250 0.3826 0.00772 0.00145 -0.0839 0.6495 0.3785
0.000 0.4104 0.00759 0.00145 -0.0839 0.6422 0.4375
0.250 0.4381 0.00744 0.00146 -0.0839 0.6341 0.5056
0.500 0.4653 0.00725 0.00149 -0.0838 0.6262 0.5920
0.750 0.4915 0.00702 0.00154 -0.0835 0.6174 0.6944
1.000 0.5149 0.00672 0.00160 -0.0823 0.6080 0.8202
1.250 0.5486 0.00650 0.00157 -0.0831 0.5968 1.0000
1.500 0.5763 0.00661 0.00160 -0.0830 0.5855 1.0000
1.750 0.6042 0.00670 0.00163 -0.0830 0.5743 1.0000
2.000 0.6319 0.00681 0.00168 -0.0829 0.5631 1.0000
2.250 0.6595 0.00693 0.00174 -0.0829 0.5514 1.0000
2.500 0.6870 0.00706 0.00181 -0.0828 0.5391 1.0000
2.750 0.7144 0.00720 0.00189 -0.0827 0.5262 1.0000
3.000 0.7418 0.00735 0.00199 -0.0826 0.5129 1.0000
3.250 0.7691 0.00750 0.00209 -0.0825 0.4988 1.0000
3.500 0.7962 0.00767 0.00221 -0.0824 0.4841 1.0000
3.750 0.8231 0.00786 0.00233 -0.0823 0.4683 1.0000
4.000 0.8498 0.00807 0.00249 -0.0821 0.4507 1.0000
4.250 0.8764 0.00829 0.00265 -0.0820 0.4320 1.0000
4.500 0.9025 0.00855 0.00283 -0.0818 0.4116 1.0000
4.750 0.9285 0.00884 0.00304 -0.0815 0.3902 1.0000
5.000 0.9540 0.00915 0.00327 -0.0813 0.3667 1.0000
5.250 0.9793 0.00949 0.00352 -0.0810 0.3418 1.0000
5.500 1.0041 0.00988 0.00381 -0.0806 0.3154 1.0000
5.750 1.0285 0.01031 0.00412 -0.0802 0.2889 1.0000
6.000 1.0521 0.01080 0.00447 -0.0797 0.2586 1.0000
6.250 1.0754 0.01132 0.00485 -0.0792 0.2298 1.0000
6.500 1.0988 0.01180 0.00524 -0.0787 0.2060 1.0000
6.750 1.1217 0.01233 0.00565 -0.0782 0.1803 1.0000
7.000 1.1442 0.01286 0.00608 -0.0775 0.1573 1.0000
7.250 1.1667 0.01338 0.00651 -0.0769 0.1380 1.0000
7.500 1.1884 0.01395 0.00699 -0.0762 0.1178 1.0000
7.750 1.2098 0.01452 0.00749 -0.0755 0.0997 1.0000
8.000 1.2307 0.01512 0.00801 -0.0746 0.0844 1.0000
8.250 1.2509 0.01573 0.00856 -0.0737 0.0694 1.0000
8.500 1.2704 0.01638 0.00916 -0.0727 0.0559 1.0000
8.750 1.2892 0.01705 0.00978 -0.0716 0.0446 1.0000
9.000 1.3072 0.01774 0.01044 -0.0704 0.0354 1.0000
9.250 1.3244 0.01845 0.01113 -0.0691 0.0276 1.0000
9.500 1.3398 0.01922 0.01188 -0.0675 0.0203 1.0000
9.750 1.3525 0.02002 0.01268 -0.0655 0.0154 1.0000
10.000 1.3644 0.02078 0.01348 -0.0634 0.0132 1.0000
10.250 1.3756 0.02162 0.01436 -0.0613 0.0119 1.0000
10.500 1.3869 0.02249 0.01530 -0.0593 0.0111 1.0000
10.750 1.3983 0.02339 0.01629 -0.0576 0.0105 1.0000
11.000 1.4089 0.02440 0.01737 -0.0559 0.0100 1.0000
11.250 1.4184 0.02553 0.01859 -0.0542 0.0095 1.0000
11.500 1.4268 0.02679 0.01992 -0.0525 0.0091 1.0000
11.750 1.4327 0.02830 0.02152 -0.0508 0.0086 1.0000
12.000 1.4401 0.02976 0.02307 -0.0494 0.0085 1.0000
12.250 1.4474 0.03127 0.02468 -0.0481 0.0083 1.0000
12.500 1.4535 0.03293 0.02645 -0.0469 0.0081 1.0000
12.750 1.4582 0.03480 0.02843 -0.0458 0.0080 1.0000
13.000 1.4625 0.03676 0.03050 -0.0448 0.0078 1.0000
13.250 1.4654 0.03894 0.03280 -0.0439 0.0077 1.0000
13.500 1.4674 0.04129 0.03526 -0.0432 0.0075 1.0000
13.750 1.4687 0.04379 0.03788 -0.0427 0.0074 1.0000
14.000 1.4689 0.04652 0.04071 -0.0423 0.0073 1.0000
14.250 1.4681 0.04944 0.04375 -0.0422 0.0071 1.0000
14.500 1.4662 0.05262 0.04705 -0.0422 0.0070 1.0000
14.750 1.4641 0.05597 0.05052 -0.0425 0.0069 1.0000
15.000 1.4603 0.05967 0.05434 -0.0430 0.0068 1.0000
15.250 1.4558 0.06365 0.05843 -0.0438 0.0067 1.0000
15.500 1.4508 0.06784 0.06273 -0.0448 0.0065 1.0000
15.750 1.4442 0.07242 0.06744 -0.0461 0.0065 1.0000
16.000 1.4353 0.07751 0.07265 -0.0477 0.0064 1.0000
16.250 1.4259 0.08286 0.07813 -0.0496 0.0063 1.0000
16.500 1.4149 0.08864 0.08403 -0.0518 0.0062 1.0000
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Polar data table (+)
Polar graphs
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