EPPLER 584 AIRFOIL (e584-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 584 AIRFOIL (e584-il) Reynolds number: 50,000 Max Cl/Cd: 4.48 at α=11° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e584-il-50000.txt Download as CSV file: xf-e584-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 584 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.4685 0.13409 0.12922 -0.0169 1.0000 0.2277
-8.000 -0.4321 0.12894 0.12402 -0.0161 0.9976 0.2387
-7.750 -0.4754 0.12878 0.12400 -0.0152 0.9979 0.2448
-7.500 -0.4432 0.12415 0.11933 -0.0156 0.9943 0.2585
-7.000 -0.4679 0.12021 0.11552 -0.0117 0.9944 0.2769
-6.750 -0.5176 0.12003 0.11548 -0.0057 1.0000 0.2790
-6.500 -0.5744 0.11921 0.11479 -0.0033 1.0000 0.2802
-6.250 -0.5153 0.11435 0.10989 -0.0010 1.0000 0.3029
-6.000 -0.5496 0.11314 0.10877 0.0022 1.0000 0.3132
-5.750 -0.5485 0.11053 0.10620 0.0051 1.0000 0.3292
-5.500 -0.5562 0.10819 0.10391 0.0084 1.0000 0.3458
-3.750 -0.4404 0.09477 0.09060 0.0337 1.0000 0.6492
-3.500 -0.5996 0.07072 0.06491 -0.0102 1.0000 0.2268
-3.250 -0.5535 0.06122 0.05387 -0.0146 1.0000 0.1230
-3.000 -0.5295 0.05781 0.04956 -0.0143 1.0000 0.1109
-2.750 -0.5106 0.05537 0.04680 -0.0138 1.0000 0.1097
-2.500 -0.4903 0.05323 0.04427 -0.0133 1.0000 0.1088
-2.250 -0.4694 0.05139 0.04205 -0.0127 1.0000 0.1079
-2.000 -0.4477 0.04975 0.04003 -0.0120 1.0000 0.1074
-1.750 -0.4258 0.04847 0.03837 -0.0112 1.0000 0.1084
-1.500 -0.4038 0.04749 0.03698 -0.0103 1.0000 0.1134
-1.250 -0.3838 0.04663 0.03614 -0.0096 1.0000 0.1208
-1.000 -0.3624 0.04606 0.03537 -0.0085 1.0000 0.1298
-0.750 -0.3417 0.04573 0.03506 -0.0072 1.0000 0.1461
-0.500 -0.2122 0.04777 0.04056 -0.0152 1.0000 1.0000
-0.250 -0.2036 0.04807 0.04048 -0.0132 1.0000 1.0000
0.000 -0.1953 0.04837 0.04045 -0.0114 1.0000 1.0000
0.250 -0.1871 0.04870 0.04051 -0.0096 1.0000 1.0000
0.500 -0.1788 0.04903 0.04060 -0.0078 1.0000 1.0000
0.750 -0.1705 0.04939 0.04074 -0.0061 1.0000 1.0000
1.000 -0.1619 0.04978 0.04092 -0.0044 0.9999 1.0000
1.250 -0.1340 0.05161 0.04246 -0.0067 0.9931 1.0000
1.500 -0.1075 0.05318 0.04379 -0.0086 0.9841 1.0000
1.750 -0.0849 0.05441 0.04481 -0.0098 0.9745 1.0000
2.000 -0.0637 0.05569 0.04589 -0.0107 0.9648 1.0000
2.250 -0.0402 0.05744 0.04746 -0.0120 0.9561 1.0000
2.500 -0.0161 0.05900 0.04885 -0.0133 0.9446 1.0000
2.750 -0.0001 0.05972 0.04944 -0.0132 0.9329 1.0000
3.000 0.0172 0.06092 0.05051 -0.0133 0.9228 1.0000
3.250 0.0464 0.06338 0.05281 -0.0154 0.9133 1.0000
3.500 0.0579 0.06373 0.05308 -0.0145 0.9007 1.0000
3.750 0.0751 0.06512 0.05437 -0.0146 0.8915 1.0000
4.000 0.1028 0.06734 0.05647 -0.0165 0.8809 1.0000
4.250 0.1127 0.06786 0.05693 -0.0154 0.8691 1.0000
4.500 0.1429 0.07084 0.05979 -0.0178 0.8619 1.0000
4.750 0.1546 0.07130 0.06022 -0.0171 0.8488 1.0000
5.000 0.1673 0.07251 0.06138 -0.0167 0.8389 1.0000
5.250 0.1990 0.07538 0.06418 -0.0192 0.8295 1.0000
5.500 0.2047 0.07577 0.06456 -0.0178 0.8177 1.0000
5.750 0.2332 0.07880 0.06753 -0.0199 0.8103 1.0000
6.000 0.2463 0.07969 0.06842 -0.0196 0.7973 1.0000
6.250 0.2567 0.08096 0.06968 -0.0191 0.7865 1.0000
6.500 0.2924 0.08453 0.07323 -0.0222 0.7780 1.0000
6.750 0.2953 0.08483 0.07354 -0.0207 0.7651 1.0000
7.000 0.3091 0.08670 0.07542 -0.0209 0.7558 1.0000
7.250 0.3399 0.08970 0.07842 -0.0232 0.7452 1.0000
7.500 0.3430 0.09045 0.07921 -0.0220 0.7331 1.0000
7.750 0.3615 0.09291 0.08169 -0.0229 0.7246 1.0000
8.000 0.3859 0.09540 0.08420 -0.0244 0.7131 1.0000
8.250 0.3901 0.09655 0.08539 -0.0236 0.7016 1.0000
8.500 0.4055 0.09888 0.08776 -0.0242 0.6925 1.0000
8.750 0.4355 0.10211 0.09106 -0.0263 0.6822 1.0000
9.000 0.4374 0.10318 0.09217 -0.0255 0.6705 1.0000
9.250 0.4465 0.10529 0.09434 -0.0257 0.6614 1.0000
9.500 0.4791 0.10914 0.09825 -0.0281 0.6526 1.0000
9.750 0.4780 0.11014 0.09932 -0.0273 0.6415 1.0000
10.000 0.4857 0.11244 0.10170 -0.0276 0.6334 1.0000
10.250 0.5188 0.11646 0.10580 -0.0299 0.6242 1.0000
10.500 0.5135 0.11735 0.10676 -0.0290 0.6137 1.0000
10.750 0.5229 0.11997 0.10945 -0.0296 0.6062 1.0000
11.000 0.5546 0.12392 0.11352 -0.0318 0.5959 1.0000
11.250 0.5475 0.12487 0.11454 -0.0311 0.5857 1.0000
11.500 0.5597 0.12786 0.11762 -0.0320 0.5788 1.0000
11.750 0.5847 0.13123 0.12109 -0.0335 0.5673 1.0000
12.000 0.5784 0.13264 0.12257 -0.0333 0.5581 1.0000
12.250 0.6031 0.13670 0.12676 -0.0351 0.5504 1.0000
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Polar data table (+)
Polar graphs
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