E61 (5.64%) (e61-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: E61 (5.64%) (e61-il) Reynolds number: 500,000 Max Cl/Cd: 170.99 at α=2.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e61-il-500000.txt Download as CSV file: xf-e61-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: E61 (5.64%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.3687 0.15397 0.15170 -0.0207 1.0000 0.0070
-11.500 -0.3660 0.15166 0.14940 -0.0207 1.0000 0.0070
-11.250 -0.3637 0.14934 0.14711 -0.0206 1.0000 0.0071
-8.500 -0.2178 0.10911 0.10685 -0.0544 0.9839 0.0075
-8.250 -0.2112 0.10610 0.10385 -0.0547 0.9789 0.0077
-8.000 -0.1975 0.10292 0.10067 -0.0573 0.9763 0.0079
-7.750 -0.1817 0.09965 0.09740 -0.0606 0.9744 0.0082
-7.500 -0.1641 0.09627 0.09401 -0.0645 0.9729 0.0085
-7.250 -0.1450 0.09289 0.09064 -0.0688 0.9718 0.0090
-7.000 -0.1416 0.09049 0.08825 -0.0687 0.9643 0.0096
-6.750 -0.1247 0.08732 0.08508 -0.0723 0.9618 0.0100
-4.750 0.0635 0.05667 0.05435 -0.1177 0.9277 0.0121
-4.500 0.0937 0.05295 0.05061 -0.1231 0.9258 0.0126
-4.250 0.1309 0.04923 0.04685 -0.1300 0.9245 0.0132
-4.000 0.1764 0.04509 0.04265 -0.1392 0.9236 0.0142
-3.750 0.2311 0.04034 0.03780 -0.1506 0.9231 0.0161
-1.500 0.6839 0.01128 0.00611 -0.2100 0.9134 0.0279
-1.250 0.7253 0.01013 0.00481 -0.2129 0.9122 0.0257
-1.000 0.7673 0.00934 0.00394 -0.2158 0.9107 0.0254
-0.750 0.8109 0.00878 0.00331 -0.2192 0.9092 0.0275
-0.500 0.8392 0.00854 0.00302 -0.2192 0.9012 0.0293
-0.250 0.8808 0.00820 0.00265 -0.2221 0.8975 0.0380
0.000 0.9158 0.00781 0.00254 -0.2239 0.8903 0.1671
0.250 0.9560 0.00733 0.00253 -0.2269 0.8843 0.3926
0.500 0.9793 0.00637 0.00268 -0.2259 0.8748 1.0000
0.750 1.0124 0.00637 0.00260 -0.2270 0.8657 1.0000
1.000 1.0449 0.00640 0.00253 -0.2279 0.8559 1.0000
1.250 1.0728 0.00647 0.00254 -0.2279 0.8441 1.0000
1.500 1.1007 0.00656 0.00256 -0.2278 0.8322 1.0000
1.750 1.1282 0.00667 0.00261 -0.2277 0.8202 1.0000
2.000 1.1552 0.00679 0.00270 -0.2274 0.8079 1.0000
2.250 1.1815 0.00692 0.00278 -0.2270 0.7946 1.0000
2.500 1.2072 0.00706 0.00287 -0.2265 0.7806 1.0000
2.750 1.2325 0.00722 0.00299 -0.2259 0.7663 1.0000
3.000 1.2572 0.00739 0.00315 -0.2252 0.7510 1.0000
3.250 1.2813 0.00759 0.00329 -0.2243 0.7339 1.0000
3.500 1.3045 0.00779 0.00345 -0.2232 0.7144 1.0000
3.750 1.3270 0.00803 0.00364 -0.2220 0.6929 1.0000
4.000 1.3487 0.00829 0.00384 -0.2207 0.6680 1.0000
4.250 1.3684 0.00864 0.00407 -0.2188 0.6358 1.0000
4.500 1.3809 0.00931 0.00445 -0.2155 0.5688 1.0000
4.750 1.3864 0.01052 0.00505 -0.2110 0.4627 1.0000
5.000 1.3959 0.01177 0.00575 -0.2075 0.3668 1.0000
5.250 1.4106 0.01276 0.00637 -0.2052 0.2990 1.0000
5.500 1.4254 0.01379 0.00703 -0.2029 0.2339 1.0000
5.750 1.4375 0.01504 0.00783 -0.2002 0.1574 1.0000
6.000 1.4466 0.01656 0.00882 -0.1970 0.0772 1.0000
6.250 1.4538 0.01828 0.01010 -0.1933 0.0137 1.0000
6.500 1.4707 0.01907 0.01094 -0.1911 0.0090 1.0000
6.750 1.4869 0.01995 0.01194 -0.1888 0.0073 1.0000
7.000 1.4996 0.02120 0.01339 -0.1858 0.0066 1.0000
7.250 1.5126 0.02232 0.01465 -0.1830 0.0065 1.0000
7.500 1.5240 0.02361 0.01607 -0.1800 0.0064 1.0000
7.750 1.5336 0.02509 0.01770 -0.1767 0.0063 1.0000
8.000 1.5415 0.02680 0.01956 -0.1732 0.0064 1.0000
8.250 1.5491 0.02885 0.02179 -0.1698 0.0064 1.0000
8.500 1.5582 0.03151 0.02462 -0.1667 0.0065 1.0000
8.750 1.5739 0.03356 0.02680 -0.1647 0.0067 1.0000
9.000 1.5898 0.03490 0.02826 -0.1628 0.0069 1.0000
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Polar data table (+)
Polar graphs
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