EPPLER 331 AIRFOIL (e331-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 331 AIRFOIL (e331-il) Reynolds number: 200,000 Max Cl/Cd: 64.87 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e331-il-200000-n5.txt Download as CSV file: xf-e331-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 331 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.4632 0.09230 0.08901 -0.0065 1.0000 0.0200
-8.750 -0.4650 0.08807 0.08482 -0.0091 1.0000 0.0201
-8.500 -0.4700 0.08341 0.08021 -0.0127 1.0000 0.0200
-8.250 -0.4783 0.07894 0.07576 -0.0156 1.0000 0.0201
-8.000 -0.4877 0.07516 0.07197 -0.0164 1.0000 0.0200
-7.750 -0.4968 0.07173 0.06852 -0.0158 1.0000 0.0200
-7.500 -0.5008 0.06811 0.06485 -0.0155 1.0000 0.0203
-6.750 -0.5067 0.05234 0.04852 -0.0112 0.9787 0.0116
-6.500 -0.4793 0.04806 0.04393 -0.0145 0.8826 0.0112
-6.250 -0.4671 0.04460 0.04010 -0.0131 0.8349 0.0109
-5.750 -0.4463 0.03754 0.03225 -0.0078 0.7766 0.0104
-5.250 -0.4184 0.03100 0.02479 -0.0024 0.7357 0.0104
-5.000 -0.4006 0.02790 0.02110 0.0003 0.7181 0.0114
-4.750 -0.3806 0.02530 0.01787 0.0025 0.7013 0.0119
-4.500 -0.3584 0.02348 0.01569 0.0039 0.6848 0.0121
-4.250 -0.3337 0.02175 0.01356 0.0051 0.6693 0.0120
-4.000 -0.3080 0.02035 0.01185 0.0059 0.6542 0.0120
-3.750 -0.2817 0.01913 0.01040 0.0065 0.6399 0.0122
-3.500 -0.2556 0.01810 0.00919 0.0072 0.6262 0.0123
-3.250 -0.2301 0.01722 0.00818 0.0079 0.6131 0.0127
-3.000 -0.2052 0.01648 0.00731 0.0087 0.6001 0.0131
-2.750 -0.1811 0.01582 0.00654 0.0096 0.5881 0.0137
-2.500 -0.1574 0.01527 0.00587 0.0106 0.5768 0.0145
-2.250 -0.1338 0.01481 0.00530 0.0116 0.5659 0.0156
-2.000 -0.1096 0.01443 0.00484 0.0125 0.5546 0.0188
-1.750 -0.0857 0.01406 0.00444 0.0134 0.5445 0.0258
-1.250 -0.0440 0.01280 0.00373 0.0160 0.5254 0.1839
-1.000 0.0126 0.01193 0.00540 0.0128 0.5139 0.9138
-0.750 0.0842 0.01284 0.00600 0.0052 0.5017 0.9374
-0.500 0.1390 0.01321 0.00614 0.0002 0.4901 0.9508
-0.250 0.1643 0.01329 0.00609 0.0008 0.4818 0.9570
0.000 0.1969 0.01326 0.00590 -0.0003 0.4735 0.9588
0.250 0.2290 0.01322 0.00575 -0.0013 0.4649 0.9607
0.500 0.2595 0.01322 0.00561 -0.0019 0.4573 0.9629
0.750 0.2887 0.01322 0.00553 -0.0023 0.4495 0.9654
1.000 0.3157 0.01325 0.00546 -0.0023 0.4428 0.9681
1.250 0.3399 0.01331 0.00546 -0.0017 0.4358 0.9710
1.500 0.3709 0.01329 0.00536 -0.0025 0.4288 0.9723
1.750 0.4015 0.01329 0.00530 -0.0032 0.4222 0.9738
2.000 0.4311 0.01330 0.00526 -0.0038 0.4154 0.9755
2.250 0.4597 0.01335 0.00523 -0.0041 0.4095 0.9772
2.500 0.4878 0.01338 0.00526 -0.0043 0.4030 0.9791
2.750 0.5145 0.01345 0.00528 -0.0043 0.3971 0.9809
3.000 0.5406 0.01353 0.00536 -0.0041 0.3913 0.9827
3.250 0.5689 0.01358 0.00540 -0.0044 0.3852 0.9841
3.750 0.6269 0.01369 0.00549 -0.0053 0.3735 0.9865
4.000 0.6552 0.01376 0.00558 -0.0057 0.3679 0.9878
4.250 0.6825 0.01386 0.00567 -0.0058 0.3626 0.9890
4.500 0.7100 0.01395 0.00580 -0.0060 0.3563 0.9903
4.750 0.7372 0.01407 0.00593 -0.0061 0.3508 0.9917
5.000 0.7640 0.01419 0.00610 -0.0062 0.3445 0.9929
5.250 0.7901 0.01431 0.00627 -0.0061 0.3385 0.9940
5.500 0.8181 0.01444 0.00642 -0.0064 0.3325 0.9950
5.750 0.8464 0.01454 0.00661 -0.0068 0.3256 0.9962
6.000 0.8733 0.01470 0.00677 -0.0069 0.3197 0.9973
6.250 0.9001 0.01483 0.00702 -0.0070 0.3122 0.9982
6.500 0.9263 0.01501 0.00723 -0.0071 0.3056 0.9992
6.750 0.9527 0.01518 0.00750 -0.0071 0.2977 1.0000
7.000 0.9746 0.01539 0.00776 -0.0062 0.2908 1.0000
7.250 0.9967 0.01559 0.00806 -0.0054 0.2824 1.0000
7.500 1.0178 0.01584 0.00834 -0.0044 0.2745 1.0000
7.750 1.0392 0.01607 0.00869 -0.0035 0.2651 1.0000
8.000 1.0599 0.01634 0.00903 -0.0025 0.2559 1.0000
8.250 1.0797 0.01666 0.00939 -0.0013 0.2463 1.0000
8.500 1.0995 0.01697 0.00980 -0.0002 0.2352 1.0000
8.750 1.1184 0.01733 0.01024 0.0011 0.2239 1.0000
9.000 1.1362 0.01774 0.01072 0.0024 0.2117 1.0000
9.250 1.1529 0.01822 0.01123 0.0040 0.1984 1.0000
9.500 1.1682 0.01875 0.01180 0.0057 0.1844 1.0000
9.750 1.1819 0.01937 0.01245 0.0076 0.1696 1.0000
10.000 1.1937 0.02005 0.01315 0.0098 0.1550 1.0000
10.250 1.2034 0.02080 0.01391 0.0122 0.1414 1.0000
10.500 1.2105 0.02161 0.01474 0.0150 0.1284 1.0000
10.750 1.2150 0.02247 0.01562 0.0182 0.1168 1.0000
11.000 1.2160 0.02338 0.01656 0.0218 0.1066 1.0000
11.250 1.2133 0.02434 0.01753 0.0259 0.0978 1.0000
11.500 1.2055 0.02520 0.01844 0.0309 0.0910 1.0000
11.750 1.1932 0.02627 0.01953 0.0359 0.0858 1.0000
12.000 1.1859 0.02762 0.02095 0.0393 0.0801 1.0000
12.250 1.1781 0.02948 0.02285 0.0415 0.0748 1.0000
12.500 1.1730 0.03157 0.02501 0.0428 0.0698 1.0000
12.750 1.1674 0.03406 0.02758 0.0435 0.0651 1.0000
13.000 1.1610 0.03687 0.03045 0.0437 0.0609 1.0000
13.250 1.1561 0.03973 0.03340 0.0437 0.0568 1.0000
13.500 1.1470 0.04317 0.03690 0.0433 0.0533 1.0000
13.750 1.1408 0.04642 0.04026 0.0428 0.0500 1.0000
14.000 1.1332 0.04991 0.04383 0.0421 0.0468 1.0000
14.250 1.1240 0.05367 0.04766 0.0412 0.0447 1.0000
14.500 1.1149 0.05753 0.05160 0.0403 0.0425 1.0000
14.750 1.1073 0.06128 0.05546 0.0393 0.0398 1.0000
15.000 1.0980 0.06540 0.05964 0.0380 0.0377 1.0000
15.250 1.0873 0.06986 0.06417 0.0365 0.0362 1.0000
15.500 1.0809 0.07388 0.06829 0.0351 0.0341 1.0000
15.750 1.0735 0.07816 0.07267 0.0336 0.0320 1.0000
16.000 1.0650 0.08269 0.07726 0.0318 0.0307 1.0000
16.250 1.0545 0.08762 0.08225 0.0298 0.0294 1.0000
16.500 1.0492 0.09186 0.08660 0.0282 0.0277 1.0000
16.750 1.0423 0.09644 0.09129 0.0263 0.0262 1.0000
17.000 1.0338 0.10140 0.09632 0.0242 0.0249 1.0000
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Polar data table (+)
Polar graphs
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