EPPLER 334 AIRFOIL (e334-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 334 AIRFOIL (e334-il) Reynolds number: 50,000 Max Cl/Cd: 27.92 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e334-il-50000-n5.txt Download as CSV file: xf-e334-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 334 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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3104 0.10185 0.09555 -0.0286 1.0000 0.1035
-8.250 -0.3281 0.10029 0.09416 -0.0321 1.0000 0.1062
-7.750 -0.3367 0.09389 0.08803 -0.0329 1.0000 0.1086
-7.500 -0.3229 0.09014 0.08435 -0.0310 1.0000 0.1116
-7.250 -0.3262 0.08761 0.08193 -0.0301 1.0000 0.1142
-7.000 -0.3333 0.08517 0.07962 -0.0298 1.0000 0.1173
-6.750 -0.3633 0.08489 0.07945 -0.0307 1.0000 0.1226
-5.500 -0.2523 0.05929 0.05288 -0.0494 0.9146 0.0515
-5.250 -0.2252 0.05513 0.04857 -0.0519 0.8965 0.0486
-4.750 -0.1708 0.04764 0.03994 -0.0547 0.8602 0.0429
-4.500 -0.1450 0.04473 0.03659 -0.0551 0.8427 0.0430
-3.750 -0.0711 0.03754 0.02811 -0.0538 0.7930 0.0429
-3.500 -0.0464 0.03550 0.02568 -0.0529 0.7775 0.0427
-3.250 -0.0209 0.03365 0.02340 -0.0520 0.7628 0.0426
-3.000 0.0059 0.03196 0.02128 -0.0510 0.7488 0.0429
-2.750 0.0328 0.03037 0.01946 -0.0505 0.7357 0.0444
-2.500 0.0608 0.02917 0.01802 -0.0500 0.7230 0.0476
-2.250 0.0903 0.02804 0.01654 -0.0493 0.7096 0.0513
-2.000 0.1234 0.02684 0.01514 -0.0494 0.6972 0.0544
-1.750 0.1548 0.02600 0.01406 -0.0492 0.6858 0.0625
-1.500 0.1822 0.02517 0.01311 -0.0486 0.6749 0.0709
-1.250 0.3325 0.02063 0.01114 -0.0683 0.6603 1.0000
-1.000 0.3545 0.02078 0.01088 -0.0672 0.6492 1.0000
-0.750 0.3769 0.02092 0.01063 -0.0661 0.6397 1.0000
-0.500 0.3986 0.02112 0.01057 -0.0650 0.6291 1.0000
-0.250 0.4212 0.02134 0.01051 -0.0642 0.6199 1.0000
0.000 0.4437 0.02154 0.01047 -0.0632 0.6109 1.0000
0.250 0.4654 0.02182 0.01056 -0.0623 0.6018 1.0000
0.500 0.4880 0.02205 0.01057 -0.0613 0.5939 1.0000
0.750 0.5091 0.02238 0.01077 -0.0603 0.5853 1.0000
1.000 0.5314 0.02264 0.01085 -0.0593 0.5780 1.0000
1.250 0.5520 0.02302 0.01113 -0.0583 0.5699 1.0000
1.500 0.5737 0.02333 0.01131 -0.0572 0.5629 1.0000
1.750 0.5944 0.02373 0.01162 -0.0561 0.5557 1.0000
2.000 0.6149 0.02412 0.01193 -0.0550 0.5485 1.0000
2.250 0.6367 0.02446 0.01215 -0.0539 0.5425 1.0000
2.500 0.6551 0.02500 0.01270 -0.0526 0.5349 1.0000
2.750 0.6770 0.02533 0.01293 -0.0515 0.5294 1.0000
3.000 0.6948 0.02592 0.01354 -0.0502 0.5223 1.0000
3.250 0.7145 0.02639 0.01398 -0.0489 0.5161 1.0000
3.500 0.7362 0.02677 0.01428 -0.0478 0.5111 1.0000
3.750 0.7512 0.02752 0.01511 -0.0462 0.5037 1.0000
4.000 0.7721 0.02793 0.01548 -0.0450 0.4983 1.0000
4.250 0.7892 0.02859 0.01620 -0.0435 0.4924 1.0000
4.500 0.8052 0.02929 0.01695 -0.0419 0.4860 1.0000
4.750 0.8274 0.02964 0.01726 -0.0408 0.4812 1.0000
5.000 0.8393 0.03061 0.01834 -0.0389 0.4746 1.0000
5.250 0.8563 0.03127 0.01903 -0.0373 0.4688 1.0000
5.500 0.8804 0.03155 0.01931 -0.0365 0.4645 1.0000
5.750 0.8857 0.03288 0.02082 -0.0339 0.4569 1.0000
6.000 0.9048 0.03345 0.02143 -0.0327 0.4517 1.0000
6.250 0.9224 0.03413 0.02214 -0.0313 0.4465 1.0000
6.500 0.9293 0.03543 0.02363 -0.0290 0.4393 1.0000
6.750 0.9524 0.03579 0.02403 -0.0281 0.4347 1.0000
7.000 0.9572 0.03727 0.02566 -0.0258 0.4277 1.0000
7.250 0.9710 0.03821 0.02668 -0.0242 0.4215 1.0000
7.500 1.0006 0.03820 0.02673 -0.0239 0.4175 1.0000
7.750 0.9877 0.04079 0.02954 -0.0204 0.4086 1.0000
8.000 1.0129 0.04101 0.02982 -0.0197 0.4037 1.0000
8.250 1.0034 0.04347 0.03244 -0.0168 0.3957 1.0000
8.500 1.0192 0.04424 0.03331 -0.0155 0.3896 1.0000
8.750 1.0232 0.04585 0.03505 -0.0136 0.3832 1.0000
9.000 1.0097 0.04849 0.03780 -0.0107 0.3751 1.0000
9.250 1.0582 0.04709 0.03652 -0.0113 0.3713 1.0000
9.500 0.9855 0.05445 0.04389 -0.0069 0.3593 1.0000
9.750 1.0063 0.05476 0.04432 -0.0059 0.3542 1.0000
10.000 0.9723 0.06077 0.05037 -0.0058 0.3428 1.0000
10.500 0.9694 0.06663 0.05641 -0.0055 0.3267 1.0000
11.000 0.9696 0.07241 0.06238 -0.0055 0.3107 1.0000
11.500 0.9201 0.08546 0.07549 -0.0089 0.2870 1.0000
11.750 0.9476 0.08458 0.07478 -0.0074 0.2830 1.0000
12.000 0.9248 0.09109 0.08131 -0.0093 0.2716 1.0000
12.250 0.9551 0.08965 0.08005 -0.0077 0.2681 1.0000
12.500 0.9314 0.09649 0.08692 -0.0099 0.2564 1.0000
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Polar data table (+)
Polar graphs
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