EPPLER 341 AIRFOIL (e341-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 341 AIRFOIL (e341-il) Reynolds number: 100,000 Max Cl/Cd: 28.69 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e341-il-100000.txt Download as CSV file: xf-e341-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 341 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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.3259 0.09870 0.09475 -0.0144 1.0000 0.0987
-9.500 -0.3519 0.09428 0.09039 -0.0198 1.0000 0.1007
-9.250 -0.3819 0.08895 0.08510 -0.0259 1.0000 0.1011
-9.000 -0.3454 0.08514 0.08138 -0.0200 1.0000 0.1045
-8.750 -0.3372 0.08174 0.07803 -0.0194 1.0000 0.1081
-8.500 -0.3458 0.07716 0.07351 -0.0217 1.0000 0.1114
-8.250 -0.3685 0.07177 0.06816 -0.0258 1.0000 0.1134
-8.000 -0.3998 0.06753 0.06392 -0.0272 1.0000 0.1150
-7.750 -0.5000 0.07464 0.07061 -0.0182 1.0000 0.1057
-7.500 -0.4962 0.07158 0.06758 -0.0175 1.0000 0.1096
-7.250 -0.5217 0.07099 0.06665 -0.0154 1.0000 0.1164
-7.000 -0.5196 0.06605 0.06185 -0.0145 1.0000 0.1190
-6.750 -0.4997 0.06245 0.05846 -0.0156 0.9881 0.1234
-6.500 -0.4753 0.05802 0.05370 -0.0200 0.9413 0.1363
-6.250 -0.4547 0.05488 0.05023 -0.0215 0.9038 0.1513
-6.000 -0.4335 0.05164 0.04694 -0.0208 0.8704 0.1597
-5.750 -0.4251 0.04921 0.04430 -0.0184 0.8420 0.1732
-5.500 -0.4160 0.04706 0.04196 -0.0159 0.8179 0.1899
-5.250 -0.4063 0.04524 0.03993 -0.0132 0.7973 0.2108
-5.000 -0.3644 0.03698 0.02954 -0.0094 0.7850 0.0704
-4.750 -0.3434 0.03459 0.02624 -0.0059 0.7684 0.0610
-4.500 -0.3200 0.03242 0.02374 -0.0045 0.7517 0.0602
-4.250 -0.2950 0.03017 0.02117 -0.0033 0.7359 0.0595
-4.000 -0.2675 0.02813 0.01882 -0.0024 0.7209 0.0587
-3.750 -0.2379 0.02643 0.01683 -0.0017 0.7066 0.0587
-3.500 -0.2071 0.02506 0.01517 -0.0012 0.6932 0.0599
-3.250 -0.1764 0.02350 0.01359 -0.0012 0.6812 0.0648
-3.000 -0.1480 0.02274 0.01270 -0.0007 0.6685 0.0730
-2.750 -0.1223 0.02152 0.01160 0.0001 0.6568 0.0859
-2.500 0.1234 0.02114 0.01375 -0.0282 0.6317 1.0000
-2.250 0.1474 0.02099 0.01342 -0.0282 0.6206 1.0000
-2.000 0.1708 0.02091 0.01310 -0.0280 0.6113 1.0000
-1.750 0.1944 0.02083 0.01281 -0.0277 0.6020 1.0000
-1.500 0.2185 0.02081 0.01263 -0.0276 0.5933 1.0000
-1.250 0.2424 0.02080 0.01244 -0.0274 0.5854 1.0000
-1.000 0.2667 0.02085 0.01234 -0.0273 0.5778 1.0000
-0.750 0.2910 0.02088 0.01225 -0.0271 0.5700 1.0000
-0.500 0.3150 0.02097 0.01217 -0.0268 0.5635 1.0000
-0.250 0.3399 0.02108 0.01222 -0.0268 0.5556 1.0000
0.000 0.3638 0.02118 0.01216 -0.0264 0.5502 1.0000
0.250 0.3889 0.02139 0.01235 -0.0265 0.5434 1.0000
0.500 0.4134 0.02155 0.01242 -0.0263 0.5370 1.0000
0.750 0.4372 0.02171 0.01241 -0.0257 0.5323 1.0000
1.000 0.4625 0.02202 0.01280 -0.0260 0.5252 1.0000
1.250 0.4868 0.02224 0.01296 -0.0257 0.5200 1.0000
1.500 0.5108 0.02246 0.01303 -0.0252 0.5158 1.0000
1.750 0.5357 0.02289 0.01358 -0.0255 0.5090 1.0000
2.000 0.5598 0.02316 0.01381 -0.0252 0.5038 1.0000
2.250 0.5839 0.02342 0.01396 -0.0247 0.5000 1.0000
2.500 0.6080 0.02401 0.01469 -0.0249 0.4939 1.0000
2.750 0.6319 0.02437 0.01506 -0.0246 0.4887 1.0000
3.000 0.6558 0.02463 0.01526 -0.0241 0.4846 1.0000
3.250 0.6791 0.02531 0.01603 -0.0241 0.4798 1.0000
3.500 0.7020 0.02594 0.01675 -0.0240 0.4742 1.0000
3.750 0.7256 0.02623 0.01702 -0.0234 0.4699 1.0000
4.000 0.7492 0.02660 0.01734 -0.0229 0.4663 1.0000
4.250 0.7693 0.02773 0.01873 -0.0229 0.4599 1.0000
4.500 0.7916 0.02820 0.01922 -0.0223 0.4553 1.0000
4.750 0.8154 0.02842 0.01940 -0.0216 0.4517 1.0000
5.000 0.8329 0.02974 0.02094 -0.0212 0.4460 1.0000
5.250 0.8520 0.03065 0.02196 -0.0206 0.4407 1.0000
5.500 0.8752 0.03085 0.02213 -0.0197 0.4369 1.0000
5.750 0.8948 0.03166 0.02303 -0.0189 0.4326 1.0000
6.000 0.9060 0.03344 0.02506 -0.0180 0.4258 1.0000
6.250 0.9281 0.03370 0.02533 -0.0170 0.4217 1.0000
6.500 0.9542 0.03361 0.02517 -0.0162 0.4187 1.0000
6.750 0.9517 0.03671 0.02867 -0.0145 0.4106 1.0000
7.000 0.9723 0.03702 0.02902 -0.0133 0.4062 1.0000
7.250 1.0021 0.03646 0.02837 -0.0126 0.4032 1.0000
7.500 0.9851 0.04058 0.03288 -0.0097 0.3944 1.0000
7.750 1.0077 0.04055 0.03290 -0.0085 0.3901 1.0000
8.000 1.0448 0.03929 0.03154 -0.0081 0.3872 1.0000
8.250 0.9934 0.04589 0.03856 -0.0030 0.3771 1.0000
8.500 1.0313 0.04441 0.03707 -0.0024 0.3737 1.0000
8.750 1.0827 0.04200 0.03458 -0.0029 0.3711 1.0000
9.000 0.8650 0.06065 0.05344 0.0105 0.3566 1.0000
9.250 1.0358 0.04891 0.04187 0.0055 0.3571 1.0000
10.000 0.9368 0.05956 0.05261 0.0195 0.3396 1.0000
10.250 0.6730 0.08903 0.08168 0.0174 0.3193 1.0000
10.500 0.6760 0.09100 0.08369 0.0183 0.3130 1.0000
10.750 0.7328 0.08699 0.07978 0.0214 0.3095 1.0000
11.000 0.6642 0.09770 0.09045 0.0185 0.3006 1.0000
11.250 0.7081 0.09508 0.08793 0.0210 0.2954 1.0000
11.500 0.6707 0.10257 0.09541 0.0189 0.2873 1.0000
11.750 0.6968 0.10224 0.09516 0.0202 0.2816 1.0000
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Polar data table (+)
Polar graphs
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