EPPLER 583 AIRFOIL (e583-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 583 AIRFOIL (e583-il) Reynolds number: 50,000 Max Cl/Cd: 4.76 at α=9.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e583-il-50000.txt Download as CSV file: xf-e583-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 583 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
------ -------- --------- --------- -------- -------- --------
-8.000 -0.4530 0.13038 0.12552 -0.0151 1.0000 0.2380
-7.750 -0.4349 0.12663 0.12175 -0.0145 0.9980 0.2506
-7.500 -0.4720 0.12613 0.12137 -0.0132 0.9984 0.2553
-7.250 -0.4571 0.12273 0.11797 -0.0126 0.9960 0.2707
-7.000 -0.4500 0.11980 0.11507 -0.0117 0.9942 0.2855
-6.750 -0.4519 0.11735 0.11266 -0.0101 0.9933 0.2980
-6.500 -0.4905 0.11687 0.11231 -0.0041 0.9984 0.3042
-6.250 -0.4932 0.11451 0.11001 -0.0006 1.0000 0.3161
-6.000 -0.5476 0.11402 0.10966 0.0029 1.0000 0.3234
-5.750 -0.5147 0.11044 0.10607 0.0052 1.0000 0.3468
-5.500 -0.5658 0.10975 0.10549 0.0096 1.0000 0.3573
-3.500 -0.5395 0.06192 0.05434 -0.0237 1.0000 0.1247
-3.250 -0.5226 0.05857 0.05099 -0.0233 1.0000 0.1192
-3.000 -0.4962 0.05554 0.04698 -0.0234 1.0000 0.1082
-2.750 -0.4757 0.05301 0.04419 -0.0232 1.0000 0.1061
-2.500 -0.4537 0.05110 0.04184 -0.0228 1.0000 0.1062
-2.250 -0.4314 0.04966 0.03993 -0.0224 1.0000 0.1078
-2.000 -0.4091 0.04825 0.03814 -0.0218 1.0000 0.1101
-1.750 -0.3880 0.04695 0.03675 -0.0212 1.0000 0.1132
-1.500 -0.3668 0.04625 0.03587 -0.0205 1.0000 0.1210
-1.250 -0.3459 0.04550 0.03507 -0.0195 1.0000 0.1305
-1.000 -0.3256 0.04509 0.03465 -0.0181 1.0000 0.1465
-0.750 -0.3054 0.04476 0.03434 -0.0166 1.0000 0.1741
-0.500 -0.2296 0.04519 0.03832 -0.0146 1.0000 1.0000
-0.250 -0.2231 0.04523 0.03798 -0.0125 1.0000 1.0000
0.000 -0.2166 0.04528 0.03773 -0.0105 1.0000 1.0000
0.250 -0.2099 0.04537 0.03755 -0.0086 1.0000 1.0000
0.500 -0.2023 0.04553 0.03747 -0.0069 1.0000 1.0000
0.750 -0.1932 0.04580 0.03749 -0.0055 1.0000 1.0000
1.000 -0.1758 0.04664 0.03807 -0.0058 0.9975 1.0000
1.250 -0.1484 0.04829 0.03942 -0.0080 0.9904 1.0000
1.500 -0.1170 0.05058 0.04141 -0.0109 0.9829 1.0000
1.750 -0.0904 0.05198 0.04258 -0.0130 0.9728 1.0000
2.000 -0.0667 0.05323 0.04364 -0.0144 0.9626 1.0000
2.250 -0.0425 0.05473 0.04495 -0.0160 0.9531 1.0000
2.500 -0.0080 0.05748 0.04746 -0.0194 0.9446 1.0000
2.750 0.0118 0.05827 0.04812 -0.0201 0.9322 1.0000
3.000 0.0315 0.05943 0.04916 -0.0208 0.9212 1.0000
3.250 0.0647 0.06229 0.05183 -0.0239 0.9133 1.0000
3.500 0.0838 0.06316 0.05261 -0.0244 0.9004 1.0000
3.750 0.1009 0.06430 0.05366 -0.0247 0.8891 1.0000
4.000 0.1390 0.06779 0.05701 -0.0285 0.8813 1.0000
4.250 0.1502 0.06805 0.05721 -0.0278 0.8679 1.0000
4.500 0.1664 0.06940 0.05850 -0.0281 0.8575 1.0000
4.750 0.2022 0.07260 0.06160 -0.0314 0.8485 1.0000
5.000 0.2116 0.07308 0.06206 -0.0306 0.8357 1.0000
5.250 0.2294 0.07486 0.06380 -0.0312 0.8261 1.0000
5.500 0.2610 0.07763 0.06651 -0.0337 0.8157 1.0000
5.750 0.2692 0.07842 0.06729 -0.0329 0.8036 1.0000
6.000 0.2940 0.08110 0.06994 -0.0346 0.7958 1.0000
6.250 0.3146 0.08288 0.07172 -0.0356 0.7833 1.0000
6.500 0.3237 0.08412 0.07298 -0.0351 0.7720 1.0000
6.750 0.3612 0.08810 0.07693 -0.0385 0.7644 1.0000
7.000 0.3652 0.08855 0.07741 -0.0373 0.7511 1.0000
7.250 0.3754 0.09024 0.07912 -0.0372 0.7409 1.0000
7.500 0.4118 0.09401 0.08291 -0.0402 0.7319 1.0000
7.750 0.4117 0.09459 0.08354 -0.0389 0.7196 1.0000
8.000 0.4265 0.09695 0.08593 -0.0395 0.7109 1.0000
8.250 0.4547 0.09993 0.08895 -0.0415 0.6998 1.0000
8.500 0.4557 0.10110 0.09016 -0.0406 0.6885 1.0000
8.750 0.4814 0.10456 0.09367 -0.0425 0.6810 1.0000
9.000 0.4934 0.10625 0.09545 -0.0427 0.6683 1.0000
9.250 0.4973 0.10811 0.09735 -0.0424 0.6587 1.0000
9.500 0.5361 0.11256 0.10187 -0.0454 0.6497 1.0000
9.750 0.5284 0.11307 0.10245 -0.0441 0.6379 1.0000
10.000 0.5413 0.11592 0.10537 -0.0449 0.6303 1.0000
10.250 0.5660 0.11897 0.10852 -0.0463 0.6187 1.0000
10.500 0.5626 0.12052 0.11014 -0.0459 0.6088 1.0000
10.750 0.5916 0.12464 0.11435 -0.0479 0.6010 1.0000
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