S6061 9% (s6061-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: S6061 9% (s6061-il) Reynolds number: 50,000 Max Cl/Cd: 34.08 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s6061-il-50000.txt Download as CSV file: xf-s6061-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: S6061 9%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.4598 0.09572 0.08922 -0.0036 1.0000 0.2832
-7.750 -0.4648 0.09333 0.08693 -0.0038 1.0000 0.3002
-7.500 -0.4668 0.09063 0.08429 -0.0036 1.0000 0.3150
-6.250 -0.4985 0.05911 0.05236 -0.0370 1.0000 0.1464
-6.000 -0.4848 0.05357 0.04668 -0.0370 1.0000 0.1288
-5.750 -0.4763 0.04844 0.04102 -0.0374 1.0000 0.1160
-5.500 -0.4642 0.04465 0.03698 -0.0365 1.0000 0.1129
-5.250 -0.4511 0.04061 0.03238 -0.0355 1.0000 0.1083
-5.000 -0.4345 0.03737 0.02827 -0.0341 1.0000 0.1041
-4.750 -0.4161 0.03433 0.02484 -0.0327 1.0000 0.1036
-4.500 -0.3959 0.03171 0.02166 -0.0311 1.0000 0.1045
-4.250 -0.3763 0.02934 0.01931 -0.0299 1.0000 0.1112
-4.000 -0.3549 0.02732 0.01699 -0.0285 1.0000 0.1219
-3.750 -0.3326 0.02540 0.01496 -0.0270 1.0000 0.1365
-3.500 -0.3110 0.02362 0.01326 -0.0254 1.0000 0.1700
-3.250 -0.2894 0.02152 0.01162 -0.0239 1.0000 0.2482
-3.000 -0.2771 0.01837 0.01036 -0.0205 1.0000 0.4915
-2.750 -0.1027 0.01793 0.00995 -0.0351 1.0000 1.0000
-2.500 -0.1154 0.01763 0.00955 -0.0304 1.0000 1.0000
-2.250 -0.1253 0.01743 0.00922 -0.0259 1.0000 1.0000
-2.000 -0.1288 0.01731 0.00887 -0.0220 1.0000 1.0000
-1.750 -0.1257 0.01729 0.00861 -0.0191 1.0000 1.0000
-1.500 -0.1167 0.01736 0.00842 -0.0171 1.0000 1.0000
-1.250 -0.1041 0.01749 0.00831 -0.0156 1.0000 1.0000
-1.000 -0.0894 0.01768 0.00826 -0.0144 1.0000 1.0000
-0.750 -0.0735 0.01792 0.00828 -0.0135 1.0000 1.0000
-0.500 -0.0568 0.01820 0.00835 -0.0127 1.0000 1.0000
-0.250 -0.0397 0.01854 0.00850 -0.0121 1.0000 1.0000
0.000 -0.0223 0.01891 0.00872 -0.0116 1.0000 1.0000
0.250 -0.0047 0.01934 0.00900 -0.0111 1.0000 1.0000
0.500 0.0129 0.01980 0.00935 -0.0108 1.0000 1.0000
0.750 0.0305 0.02032 0.00974 -0.0105 1.0000 1.0000
1.000 0.0480 0.02089 0.01022 -0.0103 1.0000 1.0000
1.250 0.0671 0.02153 0.01078 -0.0105 0.9992 1.0000
1.500 0.1221 0.02288 0.01208 -0.0173 0.9833 1.0000
1.750 0.1701 0.02397 0.01315 -0.0227 0.9659 1.0000
2.000 0.2177 0.02503 0.01422 -0.0278 0.9481 1.0000
2.250 0.2679 0.02606 0.01532 -0.0330 0.9301 1.0000
2.500 0.3103 0.02692 0.01624 -0.0367 0.9109 1.0000
2.750 0.3534 0.02770 0.01712 -0.0401 0.8910 1.0000
3.000 0.4038 0.02838 0.01795 -0.0444 0.8715 1.0000
3.250 0.4400 0.02897 0.01871 -0.0461 0.8496 1.0000
3.500 0.4960 0.02924 0.01921 -0.0504 0.8290 1.0000
3.750 0.5321 0.02958 0.01973 -0.0514 0.8057 1.0000
4.000 0.5736 0.02962 0.02005 -0.0524 0.7832 1.0000
4.250 0.6172 0.02929 0.01997 -0.0529 0.7605 1.0000
4.500 0.6492 0.02915 0.02004 -0.0518 0.7350 1.0000
4.750 0.6825 0.02873 0.01989 -0.0503 0.7091 1.0000
5.000 0.7150 0.02813 0.01952 -0.0482 0.6817 1.0000
5.250 0.7456 0.02746 0.01904 -0.0456 0.6522 1.0000
5.500 0.7758 0.02665 0.01842 -0.0427 0.6202 1.0000
5.750 0.8008 0.02622 0.01811 -0.0395 0.5827 1.0000
6.000 0.8255 0.02578 0.01771 -0.0363 0.5411 1.0000
6.250 0.8486 0.02545 0.01732 -0.0329 0.4933 1.0000
6.500 0.8676 0.02546 0.01716 -0.0295 0.4371 1.0000
6.750 0.8821 0.02596 0.01744 -0.0260 0.3709 1.0000
7.000 0.8909 0.02707 0.01800 -0.0223 0.2928 1.0000
7.250 0.8936 0.02890 0.01917 -0.0187 0.2124 1.0000
7.500 0.9054 0.03168 0.02144 -0.0163 0.1546 1.0000
7.750 0.9296 0.03467 0.02427 -0.0151 0.1274 1.0000
8.000 0.9519 0.03734 0.02708 -0.0140 0.1118 1.0000
8.250 0.9776 0.04062 0.03033 -0.0135 0.1030 1.0000
8.500 0.9956 0.04414 0.03453 -0.0119 0.0997 1.0000
8.750 1.0098 0.04806 0.03907 -0.0104 0.0977 1.0000
9.000 1.0188 0.05216 0.04369 -0.0089 0.0965 1.0000
9.250 1.0236 0.05624 0.04820 -0.0073 0.0950 1.0000
9.500 1.0417 0.06032 0.05215 -0.0070 0.0905 1.0000
9.750 1.0400 0.06491 0.05712 -0.0056 0.0902 1.0000
10.000 0.9995 0.06985 0.06295 -0.0033 0.0952 1.0000
10.250 0.9733 0.07483 0.06817 -0.0025 0.0974 1.0000
10.500 0.9493 0.07997 0.07343 -0.0029 0.0995 1.0000
10.750 0.9293 0.08569 0.07922 -0.0047 0.1011 1.0000
11.000 0.9167 0.09173 0.08529 -0.0069 0.1024 1.0000
11.250 0.9090 0.09793 0.09154 -0.0091 0.1034 1.0000
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Polar data table (+)
Polar graphs
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