E10(08%) (e228-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: E10(08%) (e228-il) Reynolds number: 50,000 Max Cl/Cd: 28.54 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e228-il-50000-n5.txt Download as CSV file: xf-e228-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: E10(08%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.6959 0.09083 0.08414 -0.0078 1.0000 0.0456
-10.500 -0.7119 0.08295 0.07626 -0.0134 1.0000 0.0446
-10.250 -0.7332 0.07559 0.06886 -0.0188 1.0000 0.0437
-10.000 -0.7563 0.06953 0.06270 -0.0221 1.0000 0.0427
-9.750 -0.7772 0.06488 0.05789 -0.0228 1.0000 0.0424
-9.500 -0.7930 0.06079 0.05358 -0.0221 1.0000 0.0426
-9.250 -0.8021 0.05683 0.04930 -0.0212 1.0000 0.0435
-9.000 -0.8065 0.05294 0.04501 -0.0200 1.0000 0.0447
-8.750 -0.8056 0.04914 0.04073 -0.0187 1.0000 0.0460
-8.500 -0.7990 0.04547 0.03651 -0.0172 1.0000 0.0470
-8.250 -0.7870 0.04214 0.03261 -0.0157 1.0000 0.0481
-8.000 -0.7705 0.03925 0.02961 -0.0148 1.0000 0.0501
-7.750 -0.7523 0.03692 0.02702 -0.0138 1.0000 0.0528
-7.500 -0.7333 0.03491 0.02466 -0.0127 1.0000 0.0583
-7.250 -0.7140 0.03298 0.02264 -0.0117 1.0000 0.0639
-7.000 -0.6928 0.03112 0.02058 -0.0106 1.0000 0.0698
-6.750 -0.6728 0.02933 0.01870 -0.0093 1.0000 0.0769
-6.500 -0.6538 0.02774 0.01705 -0.0080 1.0000 0.0890
-6.250 -0.6355 0.02626 0.01559 -0.0068 1.0000 0.1123
-6.000 -0.6183 0.02480 0.01437 -0.0055 1.0000 0.1459
-5.750 -0.6011 0.02355 0.01330 -0.0043 1.0000 0.1960
-5.500 -0.5837 0.02251 0.01247 -0.0029 1.0000 0.2475
-5.250 -0.5659 0.02165 0.01177 -0.0014 1.0000 0.2976
-5.000 -0.5476 0.02092 0.01115 0.0002 1.0000 0.3472
-4.750 -0.5294 0.02027 0.01063 0.0019 1.0000 0.3949
-4.500 -0.5108 0.01970 0.01017 0.0037 1.0000 0.4416
-4.250 -0.4923 0.01921 0.00977 0.0056 1.0000 0.4877
-4.000 -0.4744 0.01878 0.00939 0.0078 1.0000 0.5325
-3.750 -0.4562 0.01842 0.00912 0.0100 1.0000 0.5764
-3.500 -0.4375 0.01812 0.00890 0.0122 1.0000 0.6202
-3.250 -0.4182 0.01789 0.00874 0.0144 1.0000 0.6635
-3.000 -0.3977 0.01773 0.00863 0.0165 1.0000 0.7063
-2.750 -0.3751 0.01764 0.00856 0.0182 1.0000 0.7485
-2.500 -0.3492 0.01763 0.00850 0.0192 1.0000 0.7895
-2.250 -0.3191 0.01769 0.00850 0.0194 1.0000 0.8290
-2.000 -0.2802 0.01783 0.00853 0.0178 1.0000 0.8642
-1.750 -0.2381 0.01798 0.00852 0.0153 1.0000 0.8963
-1.500 -0.1895 0.01811 0.00850 0.0113 1.0000 0.9237
-1.250 -0.1375 0.01818 0.00841 0.0063 1.0000 0.9474
-1.000 -0.0872 0.01817 0.00830 0.0012 1.0000 0.9712
-0.750 -0.0341 0.01808 0.00812 -0.0047 1.0000 0.9930
-0.500 -0.0115 0.01805 0.00803 -0.0057 0.9965 1.0000
-0.250 0.0355 0.01808 0.00801 -0.0106 0.9770 1.0000
0.000 0.0847 0.01810 0.00800 -0.0157 0.9595 1.0000
0.250 0.1334 0.01809 0.00799 -0.0204 0.9420 1.0000
0.500 0.1741 0.01807 0.00799 -0.0233 0.9207 1.0000
0.750 0.2135 0.01803 0.00799 -0.0257 0.9001 1.0000
1.000 0.2438 0.01803 0.00800 -0.0263 0.8764 1.0000
1.250 0.2714 0.01805 0.00803 -0.0261 0.8532 1.0000
1.500 0.2962 0.01808 0.00807 -0.0252 0.8304 1.0000
1.750 0.3176 0.01815 0.00819 -0.0237 0.8062 1.0000
2.000 0.3388 0.01822 0.00826 -0.0220 0.7827 1.0000
2.250 0.3596 0.01829 0.00834 -0.0201 0.7595 1.0000
2.500 0.3795 0.01839 0.00847 -0.0182 0.7346 1.0000
2.750 0.3997 0.01851 0.00864 -0.0163 0.7099 1.0000
3.000 0.4201 0.01863 0.00877 -0.0143 0.6849 1.0000
3.250 0.4406 0.01876 0.00891 -0.0123 0.6590 1.0000
3.500 0.4611 0.01892 0.00908 -0.0104 0.6319 1.0000
3.750 0.4815 0.01912 0.00928 -0.0085 0.6034 1.0000
4.000 0.5019 0.01935 0.00959 -0.0067 0.5731 1.0000
4.250 0.5223 0.01962 0.00986 -0.0049 0.5412 1.0000
4.500 0.5429 0.01992 0.01015 -0.0031 0.5079 1.0000
4.750 0.5632 0.02028 0.01048 -0.0014 0.4726 1.0000
5.000 0.5830 0.02069 0.01086 0.0003 0.4359 1.0000
5.250 0.6025 0.02119 0.01132 0.0020 0.3970 1.0000
5.500 0.6214 0.02177 0.01191 0.0036 0.3569 1.0000
5.750 0.6397 0.02245 0.01252 0.0052 0.3161 1.0000
6.000 0.6575 0.02326 0.01323 0.0067 0.2757 1.0000
6.250 0.6746 0.02420 0.01405 0.0083 0.2368 1.0000
6.500 0.6914 0.02528 0.01504 0.0097 0.2007 1.0000
6.750 0.7076 0.02649 0.01613 0.0111 0.1704 1.0000
7.000 0.7240 0.02781 0.01741 0.0126 0.1442 1.0000
7.250 0.7404 0.02922 0.01883 0.0140 0.1223 1.0000
7.500 0.7565 0.03076 0.02044 0.0154 0.1053 1.0000
7.750 0.7720 0.03233 0.02203 0.0168 0.0908 1.0000
8.000 0.7891 0.03416 0.02401 0.0183 0.0796 1.0000
8.250 0.8045 0.03607 0.02608 0.0197 0.0692 1.0000
8.500 0.8189 0.03808 0.02813 0.0210 0.0617 1.0000
8.750 0.8340 0.04055 0.03097 0.0224 0.0556 1.0000
9.000 0.8452 0.04270 0.03313 0.0237 0.0503 1.0000
9.250 0.8535 0.04554 0.03648 0.0252 0.0460 1.0000
9.500 0.8600 0.04859 0.03985 0.0267 0.0437 1.0000
9.750 0.8639 0.05151 0.04299 0.0280 0.0419 1.0000
10.000 0.8665 0.05437 0.04600 0.0291 0.0402 1.0000
10.250 0.8574 0.05800 0.04992 0.0306 0.0393 1.0000
10.500 0.8435 0.06154 0.05372 0.0318 0.0391 1.0000
10.750 0.8256 0.06576 0.05818 0.0315 0.0389 1.0000
11.000 0.8091 0.07047 0.06305 0.0299 0.0390 1.0000
11.250 0.7878 0.07639 0.06914 0.0266 0.0390 1.0000
11.500 0.7719 0.08254 0.07530 0.0229 0.0395 1.0000
11.750 0.7543 0.08967 0.08249 0.0183 0.0398 1.0000
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Polar data table (+)
Polar graphs
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