EPPLER 344 AIRFOIL (e344-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 344 AIRFOIL (e344-il) Reynolds number: 50,000 Max Cl/Cd: 14.28 at α=-1.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e344-il-50000.txt Download as CSV file: xf-e344-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 344 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 -0.2820 0.11274 0.10681 -0.0308 1.0000 0.2001
-9.000 -0.2547 0.10762 0.10173 -0.0285 1.0000 0.2111
-8.750 -0.2818 0.10716 0.10148 -0.0299 1.0000 0.2174
-8.500 -0.2594 0.10283 0.09723 -0.0277 1.0000 0.2314
-8.250 -0.2616 0.10015 0.09471 -0.0269 1.0000 0.2402
-8.000 -0.2814 0.09926 0.09406 -0.0259 1.0000 0.2512
-7.750 -0.2726 0.09649 0.09148 -0.0232 1.0000 0.2655
-7.500 -0.3101 0.09799 0.09331 -0.0170 1.0000 0.2642
-7.250 -0.3454 0.09951 0.09505 -0.0130 0.9971 0.2618
-7.000 -0.3129 0.09470 0.09025 -0.0193 0.9818 0.2933
-6.750 -0.2774 0.09042 0.08596 -0.0236 0.9660 0.3346
-6.500 -0.2393 0.08637 0.08191 -0.0261 0.9518 0.3882
-6.250 -0.1994 0.08296 0.07850 -0.0266 0.9381 0.4598
-6.000 -0.0792 0.07614 0.07156 -0.0277 0.9317 0.5906
-5.750 0.0403 0.06894 0.06424 -0.0348 0.9225 0.7437
-5.250 0.0769 0.06181 0.05696 -0.0460 0.8885 0.7087
-5.000 -0.0227 0.06133 0.05660 -0.0458 0.8665 0.5817
-4.750 -0.0886 0.05901 0.05438 -0.0462 0.8457 0.5157
-4.500 -0.1418 0.05616 0.05141 -0.0498 0.8286 0.4492
-4.250 -0.1459 0.05156 0.04525 -0.0634 0.8140 0.2475
-4.000 -0.1102 0.04847 0.04087 -0.0645 0.8033 0.1632
-3.750 -0.0925 0.04667 0.03864 -0.0625 0.7911 0.1442
-3.500 -0.0563 0.04443 0.03563 -0.0624 0.7830 0.1297
-3.250 -0.0435 0.04336 0.03438 -0.0602 0.7708 0.1272
-3.000 -0.0214 0.04211 0.03278 -0.0589 0.7612 0.1256
-2.750 0.0078 0.04070 0.03103 -0.0583 0.7521 0.1232
-2.500 0.0275 0.04013 0.03016 -0.0568 0.7423 0.1216
-2.250 0.3860 0.02892 0.02092 -0.0999 0.7324 1.0000
-2.000 0.3992 0.02976 0.02145 -0.0985 0.7220 1.0000
-1.750 0.4206 0.03008 0.02137 -0.0973 0.7146 1.0000
-1.500 0.4304 0.03118 0.02232 -0.0957 0.7048 1.0000
-1.250 0.4513 0.03160 0.02242 -0.0945 0.6981 1.0000
-1.000 0.4586 0.03297 0.02371 -0.0928 0.6899 1.0000
-0.750 0.4750 0.03371 0.02424 -0.0914 0.6830 1.0000
-0.500 0.4852 0.03492 0.02533 -0.0896 0.6763 1.0000
-0.250 0.4909 0.03639 0.02671 -0.0876 0.6692 1.0000
0.000 0.5099 0.03712 0.02724 -0.0863 0.6642 1.0000
0.250 0.5025 0.03944 0.02956 -0.0832 0.6581 1.0000
0.500 0.4974 0.04150 0.03159 -0.0801 0.6522 1.0000
0.750 0.5152 0.04237 0.03230 -0.0788 0.6474 1.0000
1.000 0.5011 0.04500 0.03491 -0.0749 0.6432 1.0000
1.250 0.4577 0.04875 0.03873 -0.0683 0.6404 1.0000
1.500 0.4105 0.05199 0.04200 -0.0607 0.6393 1.0000
1.750 0.3786 0.05456 0.04457 -0.0548 0.6392 1.0000
2.000 0.3602 0.05689 0.04685 -0.0508 0.6409 1.0000
2.250 0.3519 0.05901 0.04890 -0.0479 0.6428 1.0000
2.500 0.3524 0.06101 0.05082 -0.0459 0.6446 1.0000
2.750 0.1293 0.06587 0.05645 -0.0287 0.8269 1.0000
3.000 0.1628 0.06886 0.05920 -0.0309 0.8181 1.0000
3.250 0.1670 0.06924 0.05945 -0.0286 0.8038 1.0000
3.500 0.1753 0.07032 0.06039 -0.0269 0.7914 1.0000
3.750 0.2086 0.07350 0.06338 -0.0291 0.7838 1.0000
4.000 0.2091 0.07372 0.06351 -0.0263 0.7699 1.0000
4.250 0.2172 0.07497 0.06464 -0.0248 0.7584 1.0000
4.500 0.2498 0.07806 0.06759 -0.0268 0.7496 1.0000
4.750 0.2478 0.07833 0.06779 -0.0239 0.7368 1.0000
5.000 0.2625 0.08036 0.06972 -0.0236 0.7285 1.0000
5.250 0.2817 0.08223 0.07149 -0.0236 0.7168 1.0000
5.500 0.2848 0.08326 0.07247 -0.0218 0.7050 1.0000
5.750 0.3179 0.08673 0.07584 -0.0237 0.6978 1.0000
6.000 0.3128 0.08692 0.07599 -0.0210 0.6854 1.0000
6.250 0.3360 0.08993 0.07892 -0.0218 0.6787 1.0000
6.500 0.3440 0.09100 0.07996 -0.0206 0.6658 1.0000
6.750 0.3484 0.09253 0.08145 -0.0195 0.6568 1.0000
7.000 0.3724 0.09519 0.08407 -0.0202 0.6477 1.0000
7.250 0.3719 0.09629 0.08515 -0.0187 0.6372 1.0000
7.500 0.4034 0.09986 0.08868 -0.0202 0.6294 1.0000
7.750 0.3963 0.10033 0.08915 -0.0182 0.6183 1.0000
8.000 0.4300 0.10440 0.09320 -0.0200 0.6119 1.0000
8.250 0.4205 0.10456 0.09336 -0.0178 0.6001 1.0000
8.500 0.4584 0.10939 0.09818 -0.0200 0.5943 1.0000
8.750 0.4437 0.10893 0.09773 -0.0176 0.5825 1.0000
9.000 0.4763 0.11355 0.10235 -0.0194 0.5770 1.0000
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Polar data table (+)
Polar graphs
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