EPPLER 558 AIRFOIL (e558-il) Xfoil prediction polar at RE=50,000 Ncrit=9
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Airfoil: EPPLER 558 AIRFOIL (e558-il) Reynolds number: 50,000 Max Cl/Cd: 9.53 at α=3.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e558-il-50000.txt Download as CSV file: xf-e558-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 558 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
------ -------- --------- --------- -------- -------- --------
-10.250 -0.3037 0.12048 0.11330 -0.0285 1.0000 0.2933
-10.000 -0.2850 0.11575 0.10854 -0.0275 1.0000 0.3062
-9.750 -0.3086 0.11523 0.10816 -0.0277 1.0000 0.3111
-9.500 -0.2917 0.11101 0.10391 -0.0265 1.0000 0.3271
-9.250 -0.3872 0.09534 0.08860 -0.0399 1.0000 0.2114
-9.000 -0.3455 0.09907 0.09221 -0.0330 1.0000 0.2595
-8.750 -0.3490 0.09493 0.08812 -0.0329 1.0000 0.2583
-8.500 -0.3599 0.09107 0.08435 -0.0326 1.0000 0.2575
-8.250 -0.3773 0.08747 0.08087 -0.0319 1.0000 0.2574
-8.000 -0.3995 0.08408 0.07763 -0.0305 1.0000 0.2571
-7.750 -0.4272 0.08107 0.07479 -0.0282 1.0000 0.2563
-7.500 -0.4597 0.07794 0.07185 -0.0260 1.0000 0.2554
-7.250 -0.4937 0.07374 0.06782 -0.0255 1.0000 0.2545
-7.000 -0.5312 0.06759 0.06178 -0.0276 1.0000 0.2537
-6.750 -0.5686 0.05817 0.05227 -0.0339 1.0000 0.2570
-6.500 -0.5582 0.05967 0.05380 -0.0290 1.0000 0.2705
-6.250 -0.5600 0.05695 0.05100 -0.0290 1.0000 0.2827
-6.000 -0.5588 0.05344 0.04730 -0.0308 1.0000 0.2970
-5.750 -0.5513 0.05107 0.04474 -0.0317 1.0000 0.3126
-5.500 -0.5415 0.05295 0.04673 -0.0262 1.0000 0.3229
-5.250 -0.5324 0.05168 0.04537 -0.0256 1.0000 0.3359
-5.000 -0.5211 0.04984 0.04336 -0.0264 1.0000 0.3506
-4.750 -0.5068 0.04792 0.04122 -0.0279 1.0000 0.3660
-4.500 -0.4610 0.04807 0.04122 -0.0316 0.9865 0.3857
-4.250 -0.4177 0.04764 0.04062 -0.0355 0.9733 0.4049
-4.000 -0.3762 0.04680 0.03958 -0.0396 0.9602 0.4231
-3.500 -0.2977 0.04493 0.03728 -0.0474 0.9335 0.4578
-3.250 -0.2593 0.04400 0.03611 -0.0513 0.9201 0.4744
-3.000 -0.2271 0.04387 0.03595 -0.0520 0.9070 0.4873
-2.750 -0.1868 0.04325 0.03518 -0.0551 0.8951 0.5022
-2.500 -0.1498 0.04258 0.03435 -0.0579 0.8823 0.5172
-2.250 -0.1191 0.04197 0.03356 -0.0603 0.8691 0.5311
-2.000 -0.0850 0.04163 0.03308 -0.0623 0.8571 0.5454
-1.750 -0.0435 0.04120 0.03258 -0.0647 0.8461 0.5598
-1.500 -0.0221 0.04108 0.03239 -0.0648 0.8329 0.5716
-1.250 0.0108 0.04084 0.03200 -0.0668 0.8215 0.5861
-1.000 0.0527 0.04044 0.03149 -0.0695 0.8110 0.6025
-0.750 0.0673 0.04074 0.03179 -0.0680 0.7984 0.6130
-0.500 0.1041 0.04054 0.03153 -0.0697 0.7887 0.6286
-0.250 0.1286 0.04066 0.03160 -0.0700 0.7773 0.6429
0.000 0.1502 0.04102 0.03188 -0.0702 0.7661 0.6576
0.250 0.1894 0.04076 0.03159 -0.0717 0.7573 0.6757
0.500 0.1962 0.04164 0.03248 -0.0698 0.7456 0.6885
0.750 0.2449 0.04113 0.03190 -0.0723 0.7382 0.7105
1.000 0.2409 0.04251 0.03333 -0.0693 0.7262 0.7231
1.250 0.2909 0.04185 0.03264 -0.0713 0.7197 0.7482
1.500 0.2802 0.04370 0.03452 -0.0683 0.7076 0.7631
1.750 0.3225 0.04312 0.03399 -0.0688 0.7014 0.7916
2.000 0.3060 0.04527 0.03621 -0.0654 0.6904 0.8106
2.250 0.3453 0.04468 0.03570 -0.0653 0.6841 0.8511
2.500 0.3265 0.04691 0.03810 -0.0621 0.6744 0.8864
2.750 0.4118 0.04634 0.03755 -0.0716 0.6662 1.0000
3.000 0.4087 0.04955 0.04061 -0.0741 0.6558 1.0000
3.250 0.4736 0.04970 0.04049 -0.0799 0.6485 1.0000
3.500 0.4540 0.05337 0.04406 -0.0789 0.6405 1.0000
3.750 0.4832 0.05474 0.04528 -0.0804 0.6333 1.0000
4.000 0.4949 0.05696 0.04740 -0.0807 0.6268 1.0000
4.250 0.4899 0.05996 0.05034 -0.0801 0.6216 1.0000
4.500 0.5146 0.06159 0.05190 -0.0810 0.6154 1.0000
4.750 0.5266 0.06389 0.05414 -0.0811 0.6096 1.0000
5.000 0.5199 0.06716 0.05738 -0.0807 0.6073 1.0000
5.250 0.5197 0.07017 0.06037 -0.0807 0.6056 1.0000
5.500 0.5214 0.07322 0.06341 -0.0809 0.6055 1.0000
5.750 0.5264 0.07642 0.06661 -0.0815 0.6081 1.0000
6.000 0.5441 0.07961 0.06979 -0.0829 0.6115 1.0000
6.250 0.4411 0.08763 0.07798 -0.0834 0.7153 1.0000
6.500 0.4643 0.09013 0.08045 -0.0845 0.7042 1.0000
6.750 0.4688 0.09201 0.08233 -0.0839 0.6942 1.0000
7.000 0.5062 0.09571 0.08602 -0.0863 0.6844 1.0000
7.250 0.5007 0.09674 0.08705 -0.0847 0.6724 1.0000
7.500 0.5382 0.10108 0.09140 -0.0873 0.6655 1.0000
7.750 0.5349 0.10192 0.09225 -0.0858 0.6517 1.0000
8.000 0.5429 0.10435 0.09470 -0.0858 0.6422 1.0000
8.250 0.5699 0.10754 0.09791 -0.0871 0.6320 1.0000
8.500 0.5682 0.10931 0.09970 -0.0863 0.6208 1.0000
8.750 0.6103 0.11409 0.10454 -0.0887 0.6125 1.0000
9.000 0.5974 0.11467 0.10513 -0.0871 0.5997 1.0000
9.250 0.6185 0.11847 0.10897 -0.0882 0.5928 1.0000
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Polar data table (+)
Polar graphs
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