S1210 12% (s1210-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: S1210 12% (s1210-il) Reynolds number: 50,000 Max Cl/Cd: 14.88 at α=2.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s1210-il-50000.txt Download as CSV file: xf-s1210-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: S1210 12%
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
------ -------- --------- --------- -------- -------- --------
-7.250 -0.2320 0.12285 0.11714 -0.0197 1.0000 0.1820
-7.000 -0.2460 0.12309 0.11752 -0.0179 1.0000 0.1862
-6.750 -0.2712 0.12504 0.11965 -0.0158 1.0000 0.1878
-6.500 -0.2700 0.12198 0.11670 -0.0139 1.0000 0.1900
-6.250 -0.2661 0.11944 0.11423 -0.0115 1.0000 0.1944
-6.000 -0.2775 0.11917 0.11408 -0.0092 1.0000 0.1985
-5.750 -0.2982 0.12016 0.11522 -0.0070 1.0000 0.2014
-5.500 -0.3284 0.12228 0.11750 -0.0044 1.0000 0.2028
-5.250 -0.3353 0.12093 0.11626 -0.0037 0.9987 0.2045
-5.000 -0.2967 0.11644 0.11170 -0.0092 0.9885 0.2171
-4.750 -0.2686 0.11223 0.10749 -0.0140 0.9774 0.2245
-4.500 -0.2638 0.11238 0.10767 -0.0211 0.9618 0.2349
-4.250 -0.2327 0.10671 0.10198 -0.0220 0.9517 0.2411
-4.000 -0.2244 0.10662 0.10192 -0.0312 0.9365 0.2519
-3.750 -0.2016 0.10153 0.09683 -0.0300 0.9264 0.2557
-3.500 -0.1820 0.09875 0.09403 -0.0330 0.9152 0.2644
-3.250 -0.1590 0.09563 0.09091 -0.0402 0.9048 0.2713
-3.000 -0.1478 0.09300 0.08829 -0.0400 0.8932 0.2756
-2.750 -0.1243 0.09126 0.08653 -0.0520 0.8806 0.2859
-2.500 -0.0982 0.08699 0.08223 -0.0540 0.8730 0.2875
-2.250 -0.0861 0.08454 0.07978 -0.0551 0.8629 0.2893
-2.000 0.4236 0.04045 0.03240 -0.1956 0.8760 0.1766
-1.750 0.4506 0.04195 0.03445 -0.1945 0.8634 0.2720
-0.500 0.4736 0.04877 0.04174 -0.1658 0.8137 0.5092
-0.250 0.5077 0.04905 0.04180 -0.1682 0.8055 0.5314
0.000 0.5514 0.04911 0.04160 -0.1725 0.7978 0.5495
0.250 0.5876 0.04946 0.04178 -0.1753 0.7910 0.5626
0.500 0.6198 0.05027 0.04245 -0.1782 0.7827 0.5732
0.750 0.6871 0.04952 0.04142 -0.1853 0.7778 0.5876
1.000 0.6877 0.05207 0.04397 -0.1845 0.7683 0.5928
1.250 0.7420 0.05197 0.04370 -0.1895 0.7628 0.6062
1.500 0.7526 0.05437 0.04606 -0.1902 0.7546 0.6129
1.750 0.7885 0.05520 0.04681 -0.1929 0.7483 0.6245
2.000 0.8195 0.05649 0.04801 -0.1952 0.7423 0.6374
2.250 0.8274 0.05908 0.05061 -0.1952 0.7349 0.6466
2.500 0.8794 0.05910 0.05052 -0.1991 0.7294 0.6658
2.750 0.8676 0.06284 0.05435 -0.1971 0.7224 0.6724
3.000 0.8916 0.06439 0.05590 -0.1981 0.7159 0.6905
3.250 0.9202 0.06582 0.05733 -0.1995 0.7098 0.7133
3.500 0.9149 0.06926 0.06086 -0.1983 0.7030 0.7260
3.750 0.9583 0.06924 0.06089 -0.1999 0.6964 0.7651
4.000 0.9438 0.07334 0.06511 -0.1980 0.6895 0.7815
4.250 0.9575 0.07475 0.06668 -0.1970 0.6827 0.8277
4.500 0.9565 0.07581 0.06794 -0.1937 0.6764 0.9767
4.750 1.0008 0.07925 0.07120 -0.2010 0.6656 1.0000
5.000 1.0160 0.08284 0.07467 -0.2030 0.6562 1.0000
5.250 1.0747 0.08289 0.07452 -0.2060 0.6453 1.0000
5.500 1.0481 0.08867 0.08039 -0.2045 0.6369 1.0000
5.750 1.0784 0.09033 0.08198 -0.2052 0.6261 1.0000
6.000 1.0933 0.09297 0.08462 -0.2051 0.6154 1.0000
6.250 1.0898 0.09721 0.08890 -0.2046 0.6052 1.0000
6.500 1.1174 0.09880 0.09050 -0.2046 0.5926 1.0000
6.750 1.1669 0.09824 0.08991 -0.2046 0.5793 1.0000
7.000 1.1349 0.10502 0.09682 -0.2038 0.5680 1.0000
7.250 1.1445 0.10804 0.09987 -0.2032 0.5545 1.0000
7.500 1.1624 0.11025 0.10213 -0.2027 0.5407 1.0000
7.750 1.1857 0.11177 0.10372 -0.2020 0.5260 1.0000
8.000 1.2188 0.11215 0.10413 -0.2010 0.5118 1.0000
8.250 1.2413 0.11338 0.10543 -0.2000 0.4974 1.0000
8.500 1.2293 0.11867 0.11080 -0.1998 0.4831 1.0000
8.750 1.2297 0.12255 0.11479 -0.1994 0.4688 1.0000
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Polar data table (+)
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