E61 (5.64%) (e61-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: E61 (5.64%) (e61-il) Reynolds number: 1,000,000 Max Cl/Cd: 214.83 at α=1.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e61-il-1000000.txt Download as CSV file: xf-e61-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.1825 0.10920 0.10748 -0.0670 0.9808 0.0045
-9.000 -0.1721 0.10633 0.10461 -0.0687 0.9784 0.0047
-8.750 -0.1590 0.10322 0.10151 -0.0712 0.9768 0.0048
-8.500 -0.1443 0.10005 0.09834 -0.0742 0.9755 0.0050
-8.250 -0.1287 0.09679 0.09508 -0.0775 0.9745 0.0053
-8.000 -0.1118 0.09353 0.09182 -0.0810 0.9736 0.0058
-7.750 -0.0934 0.09008 0.08837 -0.0850 0.9728 0.0065
-7.500 -0.0726 0.08678 0.08507 -0.0897 0.9720 0.0069
-5.750 0.0431 0.06222 0.06052 -0.1164 0.9486 0.0076
-5.500 0.0553 0.05983 0.05813 -0.1175 0.9427 0.0078
-5.250 0.0813 0.05661 0.05490 -0.1226 0.9397 0.0080
-5.000 0.1146 0.05283 0.05110 -0.1299 0.9380 0.0083
-4.750 0.1520 0.04895 0.04720 -0.1380 0.9368 0.0089
-1.500 0.7647 0.00731 0.00294 -0.2260 0.9028 0.0184
-1.250 0.8058 0.00660 0.00211 -0.2290 0.8965 0.0177
-1.000 0.8386 0.00629 0.00170 -0.2301 0.8864 0.0182
-0.750 0.8707 0.00613 0.00145 -0.2310 0.8761 0.0197
-0.500 0.9014 0.00603 0.00124 -0.2316 0.8650 0.0209
-0.250 0.9302 0.00603 0.00113 -0.2318 0.8530 0.0231
0.000 0.9578 0.00606 0.00108 -0.2317 0.8408 0.0257
0.250 0.9859 0.00599 0.00111 -0.2318 0.8284 0.0939
0.500 1.0153 0.00571 0.00128 -0.2325 0.8158 0.3269
0.750 1.0432 0.00558 0.00143 -0.2328 0.8030 0.4930
1.000 1.0700 0.00514 0.00169 -0.2328 0.7907 0.8555
1.250 1.0892 0.00507 0.00171 -0.2307 0.7782 1.0000
1.500 1.1145 0.00521 0.00177 -0.2301 0.7648 1.0000
1.750 1.1395 0.00536 0.00187 -0.2295 0.7506 1.0000
2.000 1.1644 0.00551 0.00196 -0.2288 0.7364 1.0000
2.250 1.1891 0.00567 0.00206 -0.2282 0.7218 1.0000
2.500 1.2133 0.00586 0.00217 -0.2274 0.7056 1.0000
2.750 1.2372 0.00604 0.00229 -0.2265 0.6861 1.0000
3.000 1.2599 0.00628 0.00246 -0.2254 0.6636 1.0000
3.250 1.2826 0.00654 0.00262 -0.2244 0.6379 1.0000
3.500 1.3043 0.00685 0.00281 -0.2231 0.6073 1.0000
3.750 1.3220 0.00743 0.00310 -0.2210 0.5476 1.0000
4.000 1.3348 0.00849 0.00361 -0.2181 0.4451 1.0000
4.250 1.3518 0.00936 0.00408 -0.2161 0.3695 1.0000
4.500 1.3680 0.01034 0.00464 -0.2140 0.2880 1.0000
4.750 1.3863 0.01115 0.00513 -0.2123 0.2274 1.0000
5.000 1.4032 0.01208 0.00569 -0.2104 0.1631 1.0000
5.250 1.4175 0.01327 0.00643 -0.2081 0.0878 1.0000
5.500 1.4303 0.01465 0.00736 -0.2054 0.0188 1.0000
5.750 1.4499 0.01533 0.00799 -0.2038 0.0061 1.0000
6.000 1.4708 0.01585 0.00858 -0.2024 0.0050 1.0000
6.250 1.4895 0.01655 0.00938 -0.2005 0.0041 1.0000
6.500 1.5058 0.01746 0.01044 -0.1981 0.0037 1.0000
6.750 1.5197 0.01853 0.01165 -0.1954 0.0036 1.0000
7.000 1.5325 0.01964 0.01289 -0.1924 0.0036 1.0000
7.250 1.5454 0.02073 0.01408 -0.1895 0.0037 1.0000
7.500 1.5581 0.02183 0.01527 -0.1867 0.0037 1.0000
7.750 1.5710 0.02291 0.01644 -0.1840 0.0038 1.0000
8.000 1.5847 0.02396 0.01759 -0.1814 0.0039 1.0000
8.250 1.5966 0.02531 0.01904 -0.1786 0.0039 1.0000
8.500 1.6076 0.02687 0.02071 -0.1757 0.0039 1.0000
8.750 1.6176 0.02908 0.02306 -0.1728 0.0038 1.0000
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Polar data table (+)
Polar graphs
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