S6062 8% (s6062-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: S6062 8% (s6062-il) Reynolds number: 200,000 Max Cl/Cd: 58.82 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s6062-il-200000-n5.txt Download as CSV file: xf-s6062-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S6062 8%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.5262 0.08314 0.07973 -0.0144 1.0000 0.0164
-8.250 -0.5279 0.07883 0.07546 -0.0169 1.0000 0.0157
-8.000 -0.5323 0.07413 0.07083 -0.0204 1.0000 0.0152
-7.750 -0.5367 0.06815 0.06486 -0.0264 1.0000 0.0146
-7.500 -0.5381 0.06116 0.05779 -0.0318 1.0000 0.0139
-7.000 -0.5323 0.04482 0.04083 -0.0377 1.0000 0.0113
-6.750 -0.5250 0.04016 0.03587 -0.0380 1.0000 0.0111
-6.500 -0.5148 0.03589 0.03125 -0.0378 1.0000 0.0109
-6.250 -0.5025 0.03203 0.02699 -0.0369 1.0000 0.0107
-6.000 -0.4888 0.02873 0.02326 -0.0356 1.0000 0.0106
-5.750 -0.4737 0.02593 0.02004 -0.0340 1.0000 0.0105
-5.500 -0.4573 0.02353 0.01724 -0.0323 1.0000 0.0105
-5.250 -0.4362 0.02146 0.01479 -0.0313 0.9986 0.0105
-5.000 -0.4032 0.01942 0.01236 -0.0326 0.9930 0.0106
-4.750 -0.3699 0.01777 0.01040 -0.0338 0.9875 0.0110
-4.500 -0.3351 0.01659 0.00903 -0.0352 0.9829 0.0116
-4.250 -0.3044 0.01517 0.00753 -0.0363 0.9761 0.0136
-3.750 -0.2392 0.01354 0.00567 -0.0384 0.9626 0.0156
-3.500 -0.2053 0.01294 0.00488 -0.0397 0.9566 0.0171
-3.250 -0.1750 0.01238 0.00427 -0.0401 0.9477 0.0208
-3.000 -0.1445 0.01169 0.00374 -0.0408 0.9396 0.0593
-2.750 -0.1161 0.01091 0.00342 -0.0413 0.9308 0.1614
-2.500 -0.0893 0.01033 0.00316 -0.0414 0.9205 0.2573
-2.250 -0.0650 0.00948 0.00301 -0.0411 0.9104 0.4322
-2.000 -0.0412 0.00889 0.00290 -0.0402 0.9005 0.5686
-1.750 -0.0180 0.00853 0.00285 -0.0388 0.8896 0.6688
-1.500 0.0050 0.00830 0.00281 -0.0372 0.8785 0.7489
-1.250 0.0286 0.00817 0.00277 -0.0356 0.8676 0.8102
-1.000 0.0534 0.00810 0.00272 -0.0343 0.8569 0.8575
-0.750 0.0810 0.00805 0.00264 -0.0336 0.8459 0.8949
-0.500 0.1125 0.00802 0.00255 -0.0339 0.8341 0.9263
-0.250 0.1487 0.00800 0.00246 -0.0353 0.8223 0.9519
0.000 0.1864 0.00798 0.00236 -0.0372 0.8097 0.9723
0.250 0.2259 0.00795 0.00225 -0.0395 0.7962 0.9892
0.500 0.2603 0.00796 0.00217 -0.0409 0.7814 1.0000
0.750 0.2838 0.00800 0.00213 -0.0400 0.7658 1.0000
1.000 0.3075 0.00806 0.00211 -0.0390 0.7494 1.0000
1.250 0.3317 0.00814 0.00211 -0.0382 0.7322 1.0000
1.500 0.3562 0.00822 0.00212 -0.0375 0.7134 1.0000
1.750 0.3810 0.00832 0.00215 -0.0367 0.6939 1.0000
2.000 0.4060 0.00843 0.00219 -0.0361 0.6738 1.0000
2.250 0.4312 0.00856 0.00227 -0.0354 0.6523 1.0000
2.500 0.4564 0.00871 0.00235 -0.0348 0.6295 1.0000
2.750 0.4817 0.00887 0.00244 -0.0342 0.6053 1.0000
3.000 0.5069 0.00906 0.00256 -0.0337 0.5791 1.0000
3.250 0.5322 0.00927 0.00272 -0.0331 0.5503 1.0000
3.500 0.5573 0.00951 0.00288 -0.0326 0.5185 1.0000
3.750 0.5811 0.00988 0.00304 -0.0318 0.4667 1.0000
4.000 0.6039 0.01039 0.00325 -0.0310 0.3969 1.0000
4.250 0.6268 0.01097 0.00356 -0.0304 0.3288 1.0000
4.500 0.6485 0.01177 0.00394 -0.0297 0.2424 1.0000
4.750 0.6713 0.01248 0.00436 -0.0292 0.1790 1.0000
5.000 0.6948 0.01313 0.00482 -0.0287 0.1319 1.0000
5.250 0.7165 0.01408 0.00543 -0.0282 0.0684 1.0000
5.500 0.7386 0.01500 0.00614 -0.0275 0.0306 1.0000
5.750 0.7621 0.01570 0.00687 -0.0269 0.0217 1.0000
6.000 0.7856 0.01640 0.00764 -0.0263 0.0189 1.0000
6.250 0.8090 0.01711 0.00846 -0.0256 0.0178 1.0000
6.500 0.8319 0.01786 0.00937 -0.0249 0.0170 1.0000
6.750 0.8539 0.01873 0.01038 -0.0241 0.0164 1.0000
7.000 0.8752 0.01971 0.01148 -0.0233 0.0159 1.0000
7.250 0.8958 0.02081 0.01275 -0.0223 0.0155 1.0000
7.500 0.9160 0.02203 0.01408 -0.0213 0.0151 1.0000
7.750 0.9361 0.02339 0.01557 -0.0203 0.0149 1.0000
8.000 0.9563 0.02475 0.01707 -0.0193 0.0144 1.0000
8.250 0.9761 0.02610 0.01853 -0.0185 0.0135 1.0000
8.500 0.9946 0.02779 0.02036 -0.0176 0.0128 1.0000
8.750 1.0124 0.02991 0.02269 -0.0166 0.0125 1.0000
9.000 1.0275 0.03272 0.02581 -0.0154 0.0122 1.0000
9.250 1.0387 0.03610 0.02958 -0.0139 0.0120 1.0000
9.500 1.0493 0.03874 0.03258 -0.0124 0.0119 1.0000
9.750 1.0562 0.04153 0.03574 -0.0108 0.0118 1.0000
10.000 1.0584 0.04452 0.03908 -0.0089 0.0118 1.0000
10.250 1.0554 0.04772 0.04262 -0.0069 0.0117 1.0000
10.500 1.0454 0.05072 0.04589 -0.0044 0.0117 1.0000
10.750 1.0319 0.05401 0.04942 -0.0026 0.0117 1.0000
11.000 1.0164 0.05784 0.05347 -0.0021 0.0117 1.0000
11.250 1.0004 0.06226 0.05808 -0.0030 0.0118 1.0000
11.500 0.9824 0.06754 0.06356 -0.0053 0.0118 1.0000
11.750 0.9640 0.07377 0.06996 -0.0091 0.0118 1.0000
12.000 0.9451 0.08112 0.07745 -0.0142 0.0119 1.0000
12.250 0.8367 0.08317 0.07981 -0.0140 0.0121 1.0000
12.500 0.8172 0.09157 0.08835 -0.0190 0.0123 1.0000
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Polar data table (+)
Polar graphs
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