EPPLER 327 AIRFOIL (e327-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 327 AIRFOIL (e327-il) Reynolds number: 50,000 Max Cl/Cd: 17.78 at α=1.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e327-il-50000.txt Download as CSV file: xf-e327-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 327 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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4056 0.10708 0.10070 -0.0036 1.0000 0.2820
-9.000 -0.4011 0.10408 0.09777 -0.0030 1.0000 0.2991
-8.750 -0.4123 0.10187 0.09567 -0.0026 1.0000 0.3201
-8.500 -0.3907 0.09793 0.09176 -0.0008 1.0000 0.3424
-8.250 -0.4043 0.09636 0.09032 0.0005 1.0000 0.3687
-8.000 -0.3948 0.09359 0.08762 0.0031 1.0000 0.4008
-7.750 -0.3531 0.08925 0.08327 0.0056 1.0000 0.4396
-7.500 -0.3340 0.08646 0.08053 0.0086 1.0000 0.4860
-7.250 -0.3067 0.08363 0.07772 0.0112 1.0000 0.5381
-6.250 -0.3598 0.06982 0.06449 0.0088 1.0000 0.4854
-6.000 -0.4287 0.06534 0.06035 0.0075 1.0000 0.4380
-5.750 -0.4815 0.06142 0.05664 0.0079 1.0000 0.4073
-5.500 -0.5250 0.05838 0.05367 0.0092 1.0000 0.3761
-5.250 -0.5650 0.05733 0.05262 0.0141 1.0000 0.3707
-4.750 -0.5643 0.04959 0.04267 0.0102 1.0000 0.1576
-4.500 -0.5571 0.04704 0.03968 0.0126 1.0000 0.1368
-4.250 -0.5224 0.04463 0.03615 0.0119 0.9915 0.1142
-4.000 -0.4708 0.04052 0.03171 0.0071 0.9762 0.1072
-3.750 -0.4165 0.03763 0.02825 0.0027 0.9604 0.1074
-3.500 -0.3584 0.03508 0.02520 -0.0020 0.9452 0.1083
-3.250 -0.0227 0.02784 0.02079 -0.0334 0.9908 1.0000
-3.000 0.0600 0.02705 0.01927 -0.0454 0.9615 1.0000
-2.750 0.1382 0.02610 0.01777 -0.0561 0.9367 1.0000
-2.500 0.2077 0.02521 0.01646 -0.0648 0.9130 1.0000
-2.250 0.2551 0.02479 0.01570 -0.0690 0.8859 1.0000
-2.000 0.2877 0.02472 0.01536 -0.0703 0.8611 1.0000
-1.750 0.3123 0.02486 0.01528 -0.0700 0.8382 1.0000
-1.500 0.3344 0.02508 0.01528 -0.0692 0.8186 1.0000
-1.250 0.3542 0.02541 0.01545 -0.0681 0.8005 1.0000
-1.000 0.3734 0.02578 0.01569 -0.0669 0.7834 1.0000
-0.750 0.3936 0.02616 0.01593 -0.0659 0.7681 1.0000
-0.500 0.4138 0.02655 0.01620 -0.0648 0.7540 1.0000
-0.250 0.4328 0.02707 0.01663 -0.0639 0.7398 1.0000
0.000 0.4514 0.02763 0.01713 -0.0629 0.7266 1.0000
0.250 0.4699 0.02822 0.01766 -0.0618 0.7145 1.0000
0.500 0.4894 0.02870 0.01804 -0.0605 0.7041 1.0000
0.750 0.5073 0.02940 0.01872 -0.0596 0.6925 1.0000
1.000 0.5245 0.03022 0.01953 -0.0586 0.6816 1.0000
1.250 0.5449 0.03064 0.01986 -0.0572 0.6731 1.0000
1.500 0.5596 0.03175 0.02103 -0.0564 0.6618 1.0000
1.750 0.5766 0.03262 0.02189 -0.0553 0.6529 1.0000
2.000 0.5932 0.03349 0.02276 -0.0541 0.6437 1.0000
2.250 0.6062 0.03475 0.02407 -0.0530 0.6344 1.0000
2.500 0.6242 0.03548 0.02480 -0.0516 0.6265 1.0000
2.750 0.6319 0.03724 0.02664 -0.0503 0.6174 1.0000
3.000 0.6507 0.03789 0.02727 -0.0488 0.6099 1.0000
3.250 0.6514 0.04015 0.02964 -0.0471 0.6010 1.0000
3.500 0.6694 0.04092 0.03041 -0.0456 0.5941 1.0000
3.750 0.6614 0.04372 0.03330 -0.0433 0.5857 1.0000
4.000 0.6754 0.04478 0.03441 -0.0415 0.5786 1.0000
4.250 0.6596 0.04793 0.03762 -0.0385 0.5717 1.0000
4.500 0.6516 0.05033 0.04006 -0.0356 0.5648 1.0000
4.750 0.6577 0.05195 0.04170 -0.0333 0.5585 1.0000
5.000 0.6005 0.05666 0.04638 -0.0272 0.5551 1.0000
5.250 0.5509 0.05993 0.04955 -0.0204 0.5535 1.0000
5.500 0.5223 0.06253 0.05212 -0.0157 0.5519 1.0000
5.750 0.5005 0.06505 0.05460 -0.0121 0.5513 1.0000
6.000 0.4790 0.06777 0.05729 -0.0090 0.5540 1.0000
6.250 0.4690 0.07036 0.05986 -0.0070 0.5567 1.0000
6.500 0.4739 0.07301 0.06255 -0.0064 0.5597 1.0000
8.000 0.4060 0.08920 0.07873 -0.0014 0.6135 1.0000
8.250 0.4140 0.09140 0.08095 -0.0009 0.6024 1.0000
8.500 0.4414 0.09499 0.08459 -0.0020 0.5918 1.0000
8.750 0.4514 0.09695 0.08660 -0.0015 0.5776 1.0000
9.000 0.4478 0.09832 0.08798 -0.0002 0.5651 1.0000
9.250 0.4544 0.10072 0.09045 0.0001 0.5545 1.0000
9.500 0.4785 0.10433 0.09413 -0.0008 0.5434 1.0000
9.750 0.4879 0.10650 0.09637 -0.0005 0.5301 1.0000
10.000 0.4831 0.10813 0.09801 0.0003 0.5188 1.0000
10.250 0.4930 0.11100 0.10093 0.0002 0.5083 1.0000
10.500 0.5265 0.11564 0.10572 -0.0011 0.4968 1.0000
10.750 0.5127 0.11627 0.10636 0.0000 0.4850 1.0000
11.000 0.5161 0.11886 0.10900 0.0000 0.4748 1.0000
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Polar data table (+)
Polar graphs
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