E474 (14.09%) (e474-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: E474 (14.09%) (e474-il) Reynolds number: 100,000 Max Cl/Cd: 28.58 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e474-il-100000.txt Download as CSV file: xf-e474-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: E474 (14.09%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.6521 0.09194 0.08575 -0.0139 1.0000 0.1961
-10.750 -0.6567 0.08724 0.08106 -0.0150 1.0000 0.1992
-10.500 -0.9351 0.05134 0.04494 -0.0269 1.0000 0.1918
-10.250 -0.9773 0.04609 0.03924 -0.0221 1.0000 0.1951
-10.000 -0.9830 0.04340 0.03631 -0.0190 1.0000 0.1991
-9.750 -0.9454 0.04426 0.03738 -0.0191 1.0000 0.2038
-9.500 -0.9467 0.04208 0.03496 -0.0161 1.0000 0.2086
-9.250 -0.9610 0.03896 0.03132 -0.0117 1.0000 0.2134
-9.000 -0.9304 0.03887 0.03146 -0.0115 1.0000 0.2176
-8.750 -0.9148 0.03798 0.03050 -0.0097 1.0000 0.2227
-8.500 -0.9178 0.03573 0.02776 -0.0060 1.0000 0.2282
-8.250 -0.8973 0.03476 0.02687 -0.0049 1.0000 0.2324
-8.000 -0.8767 0.03418 0.02631 -0.0036 1.0000 0.2373
-7.750 -0.8683 0.03270 0.02452 -0.0009 1.0000 0.2430
-7.500 -0.8532 0.03142 0.02312 0.0009 1.0000 0.2476
-7.250 -0.8317 0.03083 0.02259 0.0021 1.0000 0.2524
-7.000 -0.8172 0.02980 0.02135 0.0041 1.0000 0.2583
-6.750 -0.8021 0.02860 0.01996 0.0061 1.0000 0.2634
-6.500 -0.7807 0.02794 0.01936 0.0072 1.0000 0.2680
-6.250 -0.7627 0.02715 0.01845 0.0089 1.0000 0.2739
-6.000 -0.7461 0.02616 0.01725 0.0107 1.0000 0.2795
-5.750 -0.7246 0.02552 0.01667 0.0118 1.0000 0.2844
-5.500 -0.7050 0.02482 0.01588 0.0133 1.0000 0.2901
-5.250 -0.6865 0.02402 0.01491 0.0148 1.0000 0.2961
-5.000 -0.6649 0.02346 0.01443 0.0159 1.0000 0.3014
-4.750 -0.6448 0.02287 0.01375 0.0173 1.0000 0.3077
-4.500 -0.6245 0.02219 0.01299 0.0186 1.0000 0.3134
-4.250 -0.6030 0.02171 0.01257 0.0197 1.0000 0.3193
-4.000 -0.5828 0.02124 0.01198 0.0210 1.0000 0.3265
-3.750 -0.5613 0.02070 0.01151 0.0221 1.0000 0.3324
-3.500 -0.5403 0.02029 0.01112 0.0233 1.0000 0.3390
-3.250 -0.5198 0.01988 0.01064 0.0244 1.0000 0.3463
-3.000 -0.4986 0.01952 0.01041 0.0255 1.0000 0.3533
-2.750 -0.4785 0.01926 0.01005 0.0267 1.0000 0.3617
-2.500 -0.4577 0.01891 0.00988 0.0277 1.0000 0.3686
-2.250 -0.4385 0.01872 0.00967 0.0289 1.0000 0.3778
-2.000 -0.4106 0.01850 0.00963 0.0283 0.9969 0.3872
-1.750 -0.3461 0.01834 0.00961 0.0210 0.9803 0.4037
-1.500 -0.2871 0.01792 0.00937 0.0151 0.9608 0.4219
-1.250 -0.2281 0.01739 0.00904 0.0095 0.9409 0.4445
-1.000 -0.1714 0.01665 0.00859 0.0048 0.9189 0.4701
-0.750 -0.1222 0.01582 0.00806 0.0018 0.8893 0.5026
-0.500 -0.0818 0.01497 0.00752 0.0009 0.8432 0.5425
-0.250 -0.0348 0.01413 0.00693 -0.0007 0.7738 0.6035
0.000 0.0000 0.01384 0.00668 0.0000 0.6820 0.6820
0.250 0.0348 0.01413 0.00693 0.0008 0.6033 0.7738
0.500 0.0818 0.01497 0.00752 -0.0009 0.5422 0.8432
0.750 0.1222 0.01582 0.00806 -0.0018 0.5024 0.8893
1.000 0.1713 0.01665 0.00859 -0.0048 0.4699 0.9188
1.250 0.2280 0.01739 0.00903 -0.0095 0.4446 0.9409
1.500 0.2870 0.01792 0.00937 -0.0151 0.4219 0.9608
1.750 0.3460 0.01833 0.00961 -0.0210 0.4037 0.9803
2.000 0.4107 0.01850 0.00962 -0.0284 0.3874 0.9970
2.250 0.4384 0.01872 0.00967 -0.0289 0.3778 1.0000
2.500 0.4577 0.01891 0.00987 -0.0277 0.3687 1.0000
2.750 0.4784 0.01926 0.01005 -0.0267 0.3617 1.0000
3.000 0.4985 0.01952 0.01040 -0.0255 0.3532 1.0000
3.250 0.5197 0.01988 0.01064 -0.0244 0.3463 1.0000
3.500 0.5402 0.02029 0.01111 -0.0232 0.3390 1.0000
3.750 0.5612 0.02070 0.01151 -0.0221 0.3323 1.0000
4.000 0.5827 0.02124 0.01198 -0.0210 0.3265 1.0000
4.250 0.6029 0.02171 0.01257 -0.0197 0.3193 1.0000
4.500 0.6244 0.02219 0.01299 -0.0186 0.3134 1.0000
4.750 0.6447 0.02287 0.01375 -0.0173 0.3077 1.0000
5.000 0.6648 0.02346 0.01443 -0.0159 0.3014 1.0000
5.250 0.6864 0.02402 0.01491 -0.0148 0.2961 1.0000
5.500 0.7050 0.02482 0.01588 -0.0133 0.2902 1.0000
5.750 0.7245 0.02551 0.01667 -0.0118 0.2844 1.0000
6.000 0.7461 0.02616 0.01725 -0.0107 0.2795 1.0000
6.250 0.7627 0.02715 0.01844 -0.0089 0.2739 1.0000
6.500 0.7806 0.02793 0.01935 -0.0072 0.2680 1.0000
6.750 0.8021 0.02860 0.01996 -0.0061 0.2634 1.0000
7.000 0.8171 0.02980 0.02134 -0.0041 0.2583 1.0000
7.250 0.8317 0.03083 0.02259 -0.0021 0.2524 1.0000
7.500 0.8531 0.03142 0.02312 -0.0009 0.2476 1.0000
7.750 0.8683 0.03270 0.02451 0.0009 0.2431 1.0000
8.000 0.8767 0.03418 0.02630 0.0036 0.2374 1.0000
8.250 0.8974 0.03475 0.02686 0.0049 0.2324 1.0000
8.500 0.9179 0.03572 0.02776 0.0060 0.2282 1.0000
8.750 0.9148 0.03799 0.03051 0.0097 0.2228 1.0000
9.000 0.9303 0.03887 0.03146 0.0115 0.2176 1.0000
9.250 0.9610 0.03895 0.03131 0.0117 0.2134 1.0000
9.500 0.9467 0.04209 0.03497 0.0161 0.2087 1.0000
9.750 0.9457 0.04423 0.03735 0.0190 0.2038 1.0000
10.000 0.9831 0.04340 0.03631 0.0190 0.1991 1.0000
10.250 0.9778 0.04607 0.03921 0.0221 0.1951 1.0000
10.500 0.9348 0.05140 0.04499 0.0269 0.1918 1.0000
10.750 0.7534 0.07093 0.06483 0.0267 0.1949 1.0000
11.000 0.9080 0.05687 0.05069 0.0323 0.1853 1.0000
11.250 0.8565 0.06315 0.05707 0.0340 0.1840 1.0000
11.500 0.8018 0.07289 0.06687 0.0304 0.1825 1.0000
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Polar data table (+)
Polar graphs
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