EPPLER 335 AIRFOIL (e335-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: EPPLER 335 AIRFOIL (e335-il) Reynolds number: 50,000 Max Cl/Cd: 25.22 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e335-il-50000-n5.txt Download as CSV file: xf-e335-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 335 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.3948 0.11067 0.10458 -0.0040 1.0000 0.0562
-10.250 -0.4943 0.11149 0.10492 -0.0017 1.0000 0.0594
-10.000 -0.5006 0.10503 0.09851 -0.0062 1.0000 0.0503
-9.750 -0.4972 0.10083 0.09436 -0.0073 1.0000 0.0483
-9.500 -0.5005 0.09570 0.08929 -0.0105 1.0000 0.0463
-9.250 -0.5328 0.08795 0.08145 -0.0173 1.0000 0.0423
-9.000 -0.5312 0.08438 0.07793 -0.0171 1.0000 0.0417
-8.750 -0.5374 0.08073 0.07429 -0.0167 1.0000 0.0410
-8.500 -0.5458 0.07732 0.07087 -0.0157 1.0000 0.0403
-8.250 -0.5556 0.07402 0.06753 -0.0140 1.0000 0.0397
-8.000 -0.5630 0.07054 0.06396 -0.0123 1.0000 0.0390
-7.750 -0.5690 0.06701 0.06031 -0.0103 1.0000 0.0382
-7.500 -0.5729 0.06353 0.05665 -0.0080 1.0000 0.0374
-7.250 -0.5753 0.05998 0.05286 -0.0053 1.0000 0.0365
-7.000 -0.5773 0.05629 0.04879 -0.0021 1.0000 0.0356
-6.750 -0.5747 0.05311 0.04517 0.0013 1.0000 0.0348
-6.500 -0.5673 0.05027 0.04210 0.0038 1.0000 0.0347
-6.250 -0.5602 0.04752 0.03901 0.0068 1.0000 0.0349
-6.000 -0.5491 0.04518 0.03661 0.0087 1.0000 0.0356
-5.750 -0.5387 0.04319 0.03453 0.0110 1.0000 0.0367
-5.500 -0.5308 0.04137 0.03257 0.0138 1.0000 0.0380
-5.250 -0.4950 0.03842 0.02915 0.0118 0.9622 0.0391
-5.000 -0.4510 0.03529 0.02545 0.0092 0.9277 0.0403
-4.750 -0.4006 0.03234 0.02189 0.0059 0.8982 0.0419
-4.500 -0.3513 0.03013 0.01948 0.0024 0.8686 0.0461
-4.250 -0.2969 0.02819 0.01718 -0.0012 0.8403 0.0524
-4.000 -0.2497 0.02681 0.01550 -0.0037 0.8133 0.0619
-3.750 -0.2173 0.02573 0.01428 -0.0038 0.7884 0.0748
-3.500 -0.1922 0.02466 0.01320 -0.0029 0.7668 0.0979
-3.250 -0.1092 0.02401 0.01584 -0.0056 0.7463 0.8800
-3.000 0.0596 0.02435 0.01484 -0.0282 0.7134 0.9956
-2.750 0.0884 0.02400 0.01410 -0.0289 0.6944 1.0000
-2.500 0.1093 0.02388 0.01366 -0.0281 0.6780 1.0000
-2.250 0.1304 0.02377 0.01328 -0.0273 0.6629 1.0000
-2.000 0.1518 0.02369 0.01295 -0.0266 0.6486 1.0000
-1.750 0.1735 0.02364 0.01265 -0.0258 0.6356 1.0000
-1.500 0.1952 0.02361 0.01239 -0.0250 0.6237 1.0000
-1.250 0.2174 0.02359 0.01220 -0.0244 0.6117 1.0000
-1.000 0.2398 0.02361 0.01205 -0.0238 0.6001 1.0000
-0.750 0.2621 0.02364 0.01191 -0.0231 0.5900 1.0000
-0.500 0.2847 0.02369 0.01183 -0.0225 0.5799 1.0000
-0.250 0.3074 0.02378 0.01181 -0.0219 0.5700 1.0000
0.000 0.3297 0.02386 0.01173 -0.0211 0.5616 1.0000
0.250 0.3524 0.02401 0.01183 -0.0206 0.5518 1.0000
0.500 0.3746 0.02414 0.01181 -0.0198 0.5443 1.0000
0.750 0.3972 0.02433 0.01200 -0.0193 0.5350 1.0000
1.000 0.4196 0.02450 0.01204 -0.0185 0.5280 1.0000
1.250 0.4428 0.02475 0.01231 -0.0181 0.5193 1.0000
1.750 0.4881 0.02526 0.01277 -0.0170 0.5044 1.0000
2.000 0.5105 0.02548 0.01291 -0.0161 0.4983 1.0000
2.250 0.5329 0.02587 0.01335 -0.0157 0.4905 1.0000
2.500 0.5551 0.02615 0.01361 -0.0149 0.4842 1.0000
2.750 0.5773 0.02653 0.01404 -0.0143 0.4774 1.0000
3.000 0.5992 0.02693 0.01448 -0.0137 0.4705 1.0000
3.250 0.6215 0.02719 0.01468 -0.0127 0.4656 1.0000
3.500 0.6426 0.02781 0.01545 -0.0123 0.4576 1.0000
3.750 0.6644 0.02815 0.01583 -0.0115 0.4521 1.0000
4.000 0.6853 0.02872 0.01650 -0.0108 0.4457 1.0000
4.250 0.7061 0.02927 0.01714 -0.0100 0.4391 1.0000
4.500 0.7279 0.02956 0.01743 -0.0090 0.4344 1.0000
4.750 0.7464 0.03048 0.01857 -0.0084 0.4268 1.0000
5.000 0.7671 0.03094 0.01909 -0.0074 0.4212 1.0000
5.250 0.7864 0.03162 0.01989 -0.0065 0.4151 1.0000
5.500 0.8045 0.03244 0.02089 -0.0055 0.4084 1.0000
5.750 0.8258 0.03275 0.02122 -0.0044 0.4036 1.0000
6.000 0.8402 0.03398 0.02271 -0.0034 0.3959 1.0000
6.250 0.8593 0.03454 0.02336 -0.0022 0.3903 1.0000
6.500 0.8759 0.03538 0.02437 -0.0009 0.3841 1.0000
6.750 0.8899 0.03644 0.02563 0.0004 0.3769 1.0000
7.000 0.9119 0.03660 0.02581 0.0017 0.3723 1.0000
7.250 0.9175 0.03847 0.02799 0.0033 0.3639 1.0000
7.500 0.9372 0.03876 0.02837 0.0048 0.3584 1.0000
7.750 0.9427 0.04046 0.03031 0.0066 0.3508 1.0000
8.000 0.9572 0.04115 0.03114 0.0084 0.3444 1.0000
8.250 0.9666 0.04230 0.03245 0.0103 0.3378 1.0000
8.500 0.9704 0.04378 0.03414 0.0126 0.3302 1.0000
8.750 0.9903 0.04385 0.03430 0.0142 0.3246 1.0000
9.000 0.9724 0.04692 0.03760 0.0175 0.3162 1.0000
9.250 1.0084 0.04555 0.03628 0.0186 0.3109 1.0000
9.500 0.9523 0.05133 0.04223 0.0237 0.3023 1.0000
9.750 0.9957 0.04921 0.04025 0.0247 0.2966 1.0000
10.000 0.8480 0.06246 0.05324 0.0304 0.2872 1.0000
10.250 0.8834 0.06020 0.05115 0.0330 0.2829 1.0000
10.500 0.8093 0.07061 0.06139 0.0320 0.2706 1.0000
10.750 0.8433 0.06800 0.05896 0.0350 0.2672 1.0000
11.000 0.7912 0.07694 0.06778 0.0334 0.2553 1.0000
11.250 0.8254 0.07414 0.06515 0.0365 0.2519 1.0000
11.500 0.7810 0.08259 0.07351 0.0345 0.2403 1.0000
12.000 0.7729 0.08833 0.07934 0.0352 0.2256 1.0000
12.500 0.7669 0.09410 0.08523 0.0356 0.2110 1.0000
12.750 0.7422 0.10068 0.09176 0.0337 0.2020 1.0000
13.000 0.7620 0.09998 0.09122 0.0355 0.1967 1.0000
13.250 0.7360 0.10719 0.09840 0.0332 0.1879 1.0000
13.500 0.7556 0.10648 0.09784 0.0349 0.1828 1.0000
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Polar data table (+)
Polar graphs
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