EPPLER 326 AIRFOIL (e326-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 326 AIRFOIL (e326-il) Reynolds number: 100,000 Max Cl/Cd: 39.44 at α=10.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e326-il-100000.txt Download as CSV file: xf-e326-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 326 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.3806 0.12711 0.12261 -0.0017 1.0000 0.0812
-11.500 -0.3803 0.12388 0.11940 -0.0031 1.0000 0.0840
-11.250 -0.4907 0.12498 0.12010 -0.0007 1.0000 0.0781
-11.000 -0.4842 0.12145 0.11659 -0.0013 1.0000 0.0805
-10.750 -0.4823 0.11776 0.11294 -0.0029 1.0000 0.0833
-10.500 -0.4877 0.11378 0.10901 -0.0061 1.0000 0.0862
-10.250 -0.5083 0.10928 0.10461 -0.0130 1.0000 0.0878
-10.000 -0.5362 0.10407 0.09944 -0.0201 1.0000 0.0882
-9.750 -0.4955 0.10034 0.09575 -0.0126 1.0000 0.0916
-9.500 -0.4890 0.09691 0.09234 -0.0125 1.0000 0.0949
-9.250 -0.4956 0.09236 0.08785 -0.0155 1.0000 0.0978
-9.000 -0.5132 0.08744 0.08297 -0.0197 1.0000 0.0997
-8.750 -0.5425 0.08378 0.07929 -0.0212 1.0000 0.1012
-8.500 -0.5770 0.08194 0.07735 -0.0189 1.0000 0.1021
-8.250 -0.6133 0.08147 0.07659 -0.0152 1.0000 0.1028
-8.000 -0.5689 0.07314 0.06866 -0.0172 1.0000 0.1072
-7.750 -0.5693 0.07023 0.06573 -0.0157 1.0000 0.1111
-7.500 -0.6074 0.07096 0.06598 -0.0106 1.0000 0.1175
-7.250 -0.5906 0.06441 0.05967 -0.0109 1.0000 0.1206
-7.000 -0.5806 0.06136 0.05668 -0.0093 1.0000 0.1261
-6.750 -0.5936 0.05925 0.05431 -0.0056 1.0000 0.1350
-6.500 -0.5806 0.05595 0.05113 -0.0041 1.0000 0.1407
-6.250 -0.5850 0.05368 0.04873 -0.0006 1.0000 0.1517
-6.000 -0.5902 0.05248 0.04736 0.0035 1.0000 0.1651
-5.750 -0.5803 0.04918 0.04429 0.0056 1.0000 0.1720
-5.000 -0.5029 0.03561 0.02816 0.0098 0.9732 0.0606
-4.750 -0.4547 0.03147 0.02364 0.0062 0.9585 0.0574
-4.500 -0.4014 0.02772 0.01913 0.0033 0.9442 0.0522
-4.250 -0.3446 0.02489 0.01602 -0.0010 0.9281 0.0522
-4.000 -0.2915 0.02267 0.01375 -0.0050 0.9070 0.0570
-3.750 -0.2451 0.02082 0.01188 -0.0076 0.8834 0.0659
-3.500 -0.2157 0.01951 0.01060 -0.0071 0.8568 0.0798
-3.250 0.0175 0.02227 0.01608 -0.0271 0.8403 0.9498
-3.000 0.1338 0.02035 0.01352 -0.0435 0.7996 1.0000
-2.750 0.1544 0.02016 0.01304 -0.0427 0.7729 1.0000
-2.500 0.1738 0.02000 0.01265 -0.0417 0.7493 1.0000
-2.250 0.1930 0.01988 0.01230 -0.0406 0.7291 1.0000
-2.000 0.2131 0.01977 0.01198 -0.0397 0.7113 1.0000
-1.750 0.2336 0.01969 0.01169 -0.0388 0.6948 1.0000
-1.500 0.2544 0.01962 0.01146 -0.0379 0.6794 1.0000
-1.250 0.2750 0.01957 0.01126 -0.0371 0.6649 1.0000
-1.000 0.2959 0.01954 0.01110 -0.0363 0.6510 1.0000
-0.750 0.3171 0.01953 0.01098 -0.0355 0.6384 1.0000
-0.500 0.3383 0.01955 0.01087 -0.0347 0.6266 1.0000
-0.250 0.3595 0.01958 0.01075 -0.0338 0.6161 1.0000
0.000 0.3812 0.01962 0.01074 -0.0331 0.6042 1.0000
0.250 0.4029 0.01969 0.01074 -0.0324 0.5939 1.0000
0.500 0.4246 0.01977 0.01069 -0.0315 0.5849 1.0000
0.750 0.4466 0.01988 0.01080 -0.0310 0.5745 1.0000
1.000 0.4685 0.02000 0.01084 -0.0302 0.5661 1.0000
1.250 0.4906 0.02012 0.01094 -0.0295 0.5567 1.0000
1.500 0.5126 0.02030 0.01110 -0.0288 0.5483 1.0000
1.750 0.5347 0.02045 0.01120 -0.0280 0.5401 1.0000
2.000 0.5567 0.02067 0.01144 -0.0274 0.5317 1.0000
2.250 0.5789 0.02084 0.01156 -0.0266 0.5242 1.0000
2.500 0.6008 0.02111 0.01189 -0.0260 0.5162 1.0000
2.750 0.6229 0.02130 0.01205 -0.0252 0.5088 1.0000
3.000 0.6447 0.02161 0.01242 -0.0245 0.5012 1.0000
3.250 0.6667 0.02184 0.01265 -0.0237 0.4939 1.0000
3.500 0.6884 0.02218 0.01305 -0.0230 0.4869 1.0000
3.750 0.7100 0.02246 0.01338 -0.0222 0.4793 1.0000
4.000 0.7318 0.02278 0.01371 -0.0214 0.4730 1.0000
4.250 0.7528 0.02316 0.01422 -0.0206 0.4651 1.0000
4.500 0.7753 0.02339 0.01439 -0.0197 0.4594 1.0000
4.750 0.7949 0.02392 0.01512 -0.0188 0.4509 1.0000
5.000 0.8176 0.02411 0.01527 -0.0180 0.4452 1.0000
5.250 0.8364 0.02471 0.01609 -0.0170 0.4367 1.0000
5.500 0.8587 0.02490 0.01626 -0.0161 0.4305 1.0000
5.750 0.8770 0.02551 0.01707 -0.0150 0.4223 1.0000
6.000 0.8989 0.02572 0.01730 -0.0140 0.4158 1.0000
6.250 0.9167 0.02634 0.01809 -0.0128 0.4076 1.0000
6.500 0.9382 0.02651 0.01828 -0.0117 0.4007 1.0000
6.750 0.9552 0.02714 0.01909 -0.0103 0.3924 1.0000
7.000 0.9767 0.02726 0.01923 -0.0092 0.3853 1.0000
7.250 0.9924 0.02792 0.02009 -0.0076 0.3765 1.0000
7.500 1.0149 0.02790 0.02004 -0.0065 0.3694 1.0000
7.750 1.0284 0.02860 0.02100 -0.0047 0.3600 1.0000
8.000 1.0535 0.02837 0.02064 -0.0038 0.3530 1.0000
8.250 1.0642 0.02908 0.02165 -0.0015 0.3428 1.0000
8.500 1.0821 0.02927 0.02191 0.0001 0.3340 1.0000
8.750 1.1018 0.02920 0.02187 0.0016 0.3247 1.0000
9.000 1.1129 0.02971 0.02259 0.0040 0.3144 1.0000
9.250 1.1307 0.02968 0.02258 0.0058 0.3047 1.0000
9.500 1.1491 0.02951 0.02240 0.0075 0.2944 1.0000
9.750 1.1566 0.02995 0.02306 0.0105 0.2830 1.0000
10.000 1.1672 0.03016 0.02338 0.0131 0.2720 1.0000
10.250 1.1791 0.03018 0.02342 0.0157 0.2606 1.0000
10.500 1.1903 0.03018 0.02338 0.0184 0.2488 1.0000
10.750 1.1928 0.03050 0.02379 0.0222 0.2370 1.0000
11.000 1.1893 0.03106 0.02449 0.0268 0.2258 1.0000
11.250 1.1856 0.03155 0.02503 0.0313 0.2152 1.0000
11.500 1.1818 0.03197 0.02540 0.0359 0.2048 1.0000
11.750 1.1738 0.03254 0.02596 0.0410 0.1949 1.0000
12.000 1.1584 0.03347 0.02699 0.0466 0.1868 1.0000
12.250 1.1506 0.03428 0.02770 0.0510 0.1775 1.0000
12.500 1.1402 0.03555 0.02900 0.0545 0.1683 1.0000
12.750 1.1305 0.03737 0.03088 0.0570 0.1593 1.0000
13.000 1.1262 0.03915 0.03260 0.0586 0.1496 1.0000
13.250 1.1211 0.04119 0.03461 0.0598 0.1404 1.0000
13.500 1.1102 0.04404 0.03759 0.0604 0.1326 1.0000
13.750 1.1089 0.04627 0.03973 0.0609 0.1239 1.0000
14.000 1.0989 0.04942 0.04299 0.0608 0.1169 1.0000
14.250 1.0956 0.05220 0.04577 0.0609 0.1098 1.0000
14.500 1.0887 0.05532 0.04895 0.0604 0.1034 1.0000
14.750 1.0854 0.05840 0.05206 0.0602 0.0974 1.0000
15.000 1.0742 0.06231 0.05612 0.0591 0.0928 1.0000
15.250 1.0812 0.06443 0.05815 0.0595 0.0865 1.0000
15.500 1.0625 0.06955 0.06352 0.0575 0.0840 1.0000
15.750 1.0512 0.07397 0.06809 0.0560 0.0808 1.0000
16.000 0.7755 0.13231 0.12702 0.0247 0.1121 1.0000
16.250 0.7352 0.14764 0.14220 0.0176 0.1118 1.0000
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Polar data table (+)
Polar graphs
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