EPPLER 344 AIRFOIL (e344-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: EPPLER 344 AIRFOIL (e344-il) Reynolds number: 50,000 Max Cl/Cd: 24.46 at α=3° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e344-il-50000-n5.txt Download as CSV file: xf-e344-il-50000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.2671 0.10754 0.10143 -0.0361 1.0000 0.1120
-9.000 -0.2936 0.10599 0.10008 -0.0399 1.0000 0.1145
-8.750 -0.3177 0.10398 0.09826 -0.0421 1.0000 0.1149
-8.500 -0.2794 0.09865 0.09299 -0.0377 1.0000 0.1182
-8.250 -0.2783 0.09599 0.09048 -0.0368 1.0000 0.1204
-8.000 -0.2856 0.09376 0.08845 -0.0361 0.9994 0.1233
-7.750 -0.3064 0.09009 0.08475 -0.0474 0.9370 0.1312
-7.500 -0.2654 0.08407 0.07877 -0.0494 0.9197 0.1365
-7.250 -0.2689 0.07341 0.06740 -0.0606 0.8904 0.0583
-7.000 -0.2424 0.06889 0.06280 -0.0636 0.8698 0.0569
-6.750 -0.2267 0.06496 0.05866 -0.0653 0.8472 0.0552
-6.250 -0.2142 0.05749 0.05017 -0.0647 0.8080 0.0488
-6.000 -0.1997 0.05461 0.04709 -0.0640 0.7904 0.0483
-5.750 -0.1867 0.05197 0.04420 -0.0629 0.7739 0.0476
-5.500 -0.1734 0.04952 0.04144 -0.0614 0.7587 0.0468
-5.250 -0.1594 0.04708 0.03865 -0.0598 0.7450 0.0461
-5.000 -0.1440 0.04473 0.03588 -0.0580 0.7323 0.0454
-4.750 -0.1282 0.04260 0.03336 -0.0562 0.7190 0.0450
-4.500 -0.1102 0.04056 0.03091 -0.0544 0.7069 0.0448
-4.250 -0.0892 0.03862 0.02851 -0.0530 0.6964 0.0447
-4.000 -0.0682 0.03694 0.02645 -0.0515 0.6848 0.0455
-3.750 -0.0445 0.03541 0.02448 -0.0502 0.6743 0.0472
-3.500 -0.0183 0.03395 0.02254 -0.0492 0.6646 0.0492
-3.250 0.0076 0.03266 0.02115 -0.0488 0.6540 0.0513
-3.000 0.0398 0.03131 0.01951 -0.0488 0.6458 0.0535
-2.750 0.0723 0.03033 0.01828 -0.0490 0.6353 0.0574
-2.500 0.1107 0.02929 0.01709 -0.0503 0.6271 0.0638
-2.250 0.1428 0.02852 0.01616 -0.0505 0.6177 0.0716
-2.000 0.1713 0.02783 0.01528 -0.0501 0.6108 0.0832
-1.750 0.3875 0.02436 0.01421 -0.0791 0.5958 1.0000
-1.500 0.4083 0.02451 0.01409 -0.0782 0.5879 1.0000
-1.250 0.4296 0.02464 0.01393 -0.0773 0.5811 1.0000
-1.000 0.4511 0.02480 0.01383 -0.0765 0.5750 1.0000
-0.750 0.4714 0.02505 0.01391 -0.0756 0.5678 1.0000
-0.500 0.4931 0.02521 0.01382 -0.0746 0.5623 1.0000
-0.250 0.5132 0.02551 0.01397 -0.0737 0.5559 1.0000
0.000 0.5334 0.02580 0.01413 -0.0727 0.5499 1.0000
0.250 0.5551 0.02602 0.01415 -0.0718 0.5452 1.0000
0.500 0.5744 0.02643 0.01446 -0.0707 0.5395 1.0000
0.750 0.5935 0.02683 0.01478 -0.0695 0.5337 1.0000
1.000 0.6146 0.02711 0.01491 -0.0685 0.5292 1.0000
1.250 0.6341 0.02753 0.01523 -0.0674 0.5246 1.0000
1.500 0.6509 0.02813 0.01583 -0.0660 0.5189 1.0000
1.750 0.6702 0.02857 0.01619 -0.0648 0.5145 1.0000
2.000 0.6917 0.02888 0.01636 -0.0638 0.5109 1.0000
2.250 0.7058 0.02966 0.01719 -0.0621 0.5055 1.0000
2.500 0.7215 0.03033 0.01786 -0.0605 0.5006 1.0000
2.750 0.7404 0.03080 0.01827 -0.0592 0.4968 1.0000
3.000 0.7619 0.03115 0.01852 -0.0582 0.4937 1.0000
3.250 0.7693 0.03233 0.01982 -0.0558 0.4882 1.0000
3.500 0.7820 0.03316 0.02069 -0.0539 0.4836 1.0000
3.750 0.7998 0.03369 0.02118 -0.0524 0.4800 1.0000
4.000 0.8212 0.03406 0.02147 -0.0514 0.4772 1.0000
4.250 0.8188 0.03574 0.02332 -0.0479 0.4716 1.0000
4.500 0.8259 0.03684 0.02447 -0.0453 0.4670 1.0000
4.750 0.8414 0.03746 0.02511 -0.0436 0.4635 1.0000
5.000 0.8632 0.03780 0.02538 -0.0425 0.4608 1.0000
5.250 0.8394 0.04047 0.02827 -0.0367 0.4544 1.0000
5.500 0.8389 0.04187 0.02971 -0.0334 0.4499 1.0000
5.750 0.8539 0.04246 0.03030 -0.0316 0.4466 1.0000
6.000 0.8776 0.04269 0.03049 -0.0307 0.4442 1.0000
6.250 0.7892 0.04834 0.03634 -0.0191 0.4343 1.0000
6.500 0.7978 0.04918 0.03717 -0.0167 0.4309 1.0000
6.750 0.8252 0.04919 0.03717 -0.0161 0.4286 1.0000
7.250 0.7378 0.05782 0.04584 -0.0062 0.4130 1.0000
7.500 0.6851 0.06483 0.05288 -0.0047 0.4012 1.0000
7.750 0.7031 0.06558 0.05363 -0.0038 0.3981 1.0000
8.000 0.7283 0.06570 0.05379 -0.0029 0.3960 1.0000
8.250 0.6857 0.07221 0.06031 -0.0025 0.3847 1.0000
8.500 0.7067 0.07282 0.06095 -0.0017 0.3817 1.0000
9.000 0.6948 0.07931 0.06750 -0.0012 0.3684 1.0000
9.250 0.7178 0.07977 0.06800 -0.0005 0.3655 1.0000
9.500 0.6955 0.08479 0.07306 -0.0009 0.3568 1.0000
9.750 0.7086 0.08629 0.07460 -0.0005 0.3522 1.0000
10.000 0.7327 0.08670 0.07508 0.0001 0.3495 1.0000
10.250 0.7093 0.09199 0.08042 -0.0006 0.3401 1.0000
10.500 0.7257 0.09321 0.08170 -0.0003 0.3361 1.0000
11.000 0.7263 0.09907 0.08767 -0.0008 0.3235 1.0000
11.250 0.7458 0.10001 0.08867 -0.0004 0.3200 1.0000
11.500 0.7344 0.10429 0.09304 -0.0013 0.3120 1.0000
11.750 0.7461 0.10606 0.09488 -0.0013 0.3071 1.0000
12.000 0.7692 0.10657 0.09546 -0.0008 0.3042 1.0000
12.250 0.7503 0.11187 0.10083 -0.0023 0.2949 1.0000
12.500 0.7691 0.11280 0.10184 -0.0020 0.2911 1.0000
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Polar data table (+)
Polar graphs
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