EPPLER 344 AIRFOIL (e344-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 344 AIRFOIL (e344-il) Reynolds number: 100,000 Max Cl/Cd: 44.01 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e344-il-100000-n5.txt Download as CSV file: xf-e344-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.2740 0.11326 0.10857 -0.0369 1.0000 0.0484
-10.000 -0.2798 0.11004 0.10544 -0.0396 1.0000 0.0487
-9.750 -0.2853 0.10667 0.10215 -0.0421 1.0000 0.0488
-9.500 -0.2862 0.10298 0.09857 -0.0432 1.0000 0.0490
-9.250 -0.2710 0.09954 0.09518 -0.0401 1.0000 0.0498
-9.000 -0.2666 0.09659 0.09231 -0.0396 1.0000 0.0505
-8.750 -0.2532 0.09258 0.08835 -0.0426 0.9820 0.0514
-8.500 -0.2299 0.08724 0.08295 -0.0502 0.9086 0.0527
-8.250 -0.2046 0.08106 0.07661 -0.0607 0.8635 0.0541
-8.000 -0.1970 0.07590 0.07124 -0.0677 0.8231 0.0553
-7.750 -0.2031 0.07232 0.06746 -0.0698 0.7923 0.0564
-7.500 -0.2291 0.07019 0.06493 -0.0701 0.7699 0.0583
-7.000 -0.2296 0.06483 0.05903 -0.0679 0.7340 0.0587
-6.500 -0.2090 0.05179 0.04560 -0.0658 0.7083 0.0281
-6.250 -0.1989 0.04939 0.04302 -0.0646 0.6947 0.0275
-6.000 -0.1890 0.04677 0.04016 -0.0630 0.6821 0.0268
-5.750 -0.1785 0.04400 0.03711 -0.0611 0.6705 0.0260
-5.250 -0.1549 0.03735 0.02943 -0.0560 0.6507 0.0236
-5.000 -0.1384 0.03521 0.02695 -0.0542 0.6407 0.0234
-4.750 -0.1204 0.03317 0.02453 -0.0525 0.6309 0.0233
-4.500 -0.1007 0.03122 0.02220 -0.0509 0.6211 0.0233
-4.250 -0.0791 0.02941 0.01996 -0.0494 0.6123 0.0233
-4.000 -0.0566 0.02804 0.01834 -0.0483 0.6027 0.0244
-3.750 -0.0328 0.02703 0.01709 -0.0475 0.5948 0.0256
-3.500 -0.0075 0.02581 0.01557 -0.0467 0.5858 0.0272
-3.250 0.0196 0.02456 0.01397 -0.0459 0.5783 0.0281
-3.000 0.0466 0.02340 0.01266 -0.0454 0.5698 0.0290
-2.750 0.0728 0.02256 0.01171 -0.0449 0.5625 0.0302
-2.500 0.0985 0.02180 0.01087 -0.0442 0.5550 0.0317
-2.250 0.1229 0.02117 0.01017 -0.0434 0.5481 0.0355
-2.000 0.1466 0.02069 0.00959 -0.0425 0.5424 0.0394
-1.750 0.1689 0.02016 0.00905 -0.0413 0.5354 0.0439
-1.500 0.1921 0.01976 0.00858 -0.0402 0.5295 0.0533
-1.250 0.2158 0.01935 0.00815 -0.0392 0.5237 0.0721
-1.000 0.2622 0.01753 0.00929 -0.0403 0.5167 0.8562
-0.750 0.4387 0.01880 0.00974 -0.0657 0.5056 0.9790
-0.500 0.4733 0.01874 0.00949 -0.0674 0.4996 0.9854
-0.250 0.5060 0.01865 0.00916 -0.0687 0.4947 0.9886
0.000 0.5367 0.01863 0.00901 -0.0696 0.4894 0.9921
0.250 0.5670 0.01863 0.00889 -0.0705 0.4842 0.9953
0.500 0.5977 0.01862 0.00872 -0.0714 0.4799 0.9982
0.750 0.6255 0.01868 0.00863 -0.0718 0.4762 1.0000
1.000 0.6471 0.01883 0.00876 -0.0709 0.4714 1.0000
1.250 0.6689 0.01898 0.00883 -0.0700 0.4671 1.0000
1.500 0.6910 0.01912 0.00887 -0.0691 0.4633 1.0000
1.750 0.7134 0.01929 0.00892 -0.0683 0.4602 1.0000
2.000 0.7346 0.01951 0.00916 -0.0674 0.4561 1.0000
2.250 0.7561 0.01971 0.00936 -0.0664 0.4522 1.0000
2.500 0.7778 0.01991 0.00950 -0.0655 0.4487 1.0000
2.750 0.8000 0.02009 0.00960 -0.0647 0.4456 1.0000
3.000 0.8213 0.02034 0.00983 -0.0637 0.4422 1.0000
3.250 0.8415 0.02062 0.01017 -0.0626 0.4384 1.0000
3.500 0.8623 0.02088 0.01044 -0.0616 0.4349 1.0000
3.750 0.8836 0.02112 0.01065 -0.0606 0.4317 1.0000
4.000 0.9056 0.02135 0.01083 -0.0598 0.4290 1.0000
4.250 0.9253 0.02168 0.01120 -0.0586 0.4257 1.0000
4.500 0.9438 0.02206 0.01166 -0.0572 0.4221 1.0000
4.750 0.9631 0.02240 0.01204 -0.0560 0.4188 1.0000
5.000 0.9833 0.02269 0.01233 -0.0548 0.4157 1.0000
5.250 1.0047 0.02295 0.01257 -0.0539 0.4130 1.0000
5.500 1.0230 0.02335 0.01302 -0.0525 0.4100 1.0000
5.750 1.0385 0.02384 0.01364 -0.0507 0.4063 1.0000
6.000 1.0554 0.02425 0.01414 -0.0490 0.4029 1.0000
6.250 1.0741 0.02458 0.01451 -0.0477 0.3999 1.0000
6.500 1.0946 0.02487 0.01478 -0.0466 0.3973 1.0000
6.750 1.1114 0.02531 0.01528 -0.0450 0.3944 1.0000
7.000 1.1220 0.02593 0.01609 -0.0424 0.3905 1.0000
7.250 1.1356 0.02640 0.01666 -0.0403 0.3869 1.0000
7.500 1.1521 0.02676 0.01707 -0.0386 0.3839 1.0000
7.750 1.1722 0.02702 0.01732 -0.0374 0.3812 1.0000
8.000 1.1831 0.02759 0.01801 -0.0349 0.3779 1.0000
8.250 1.1874 0.02830 0.01891 -0.0315 0.3739 1.0000
8.500 1.1969 0.02881 0.01952 -0.0287 0.3704 1.0000
8.750 1.2120 0.02910 0.01986 -0.0268 0.3673 1.0000
9.000 1.2338 0.02925 0.01999 -0.0258 0.3647 1.0000
9.250 1.2257 0.03020 0.02116 -0.0206 0.3606 1.0000
9.500 1.2229 0.03092 0.02203 -0.0161 0.3566 1.0000
9.750 1.2302 0.03133 0.02251 -0.0131 0.3532 1.0000
10.000 1.2503 0.03142 0.02261 -0.0119 0.3501 1.0000
10.250 1.2464 0.03223 0.02354 -0.0075 0.3463 1.0000
10.500 1.2284 0.03344 0.02492 -0.0015 0.3420 1.0000
10.750 1.2325 0.03412 0.02567 0.0013 0.3381 1.0000
11.000 1.2589 0.03403 0.02561 0.0015 0.3348 1.0000
11.250 1.2420 0.03579 0.02753 0.0058 0.3302 1.0000
11.500 1.2179 0.03836 0.03027 0.0096 0.3249 1.0000
11.750 1.2378 0.03852 0.03048 0.0102 0.3209 1.0000
12.000 1.2394 0.03993 0.03198 0.0116 0.3166 1.0000
12.250 1.1603 0.04836 0.04061 0.0138 0.3077 1.0000
12.500 1.2046 0.04623 0.03853 0.0142 0.3052 1.0000
12.750 1.0976 0.06006 0.05246 0.0129 0.2913 1.0000
13.000 1.1432 0.05711 0.04959 0.0140 0.2902 1.0000
15.250 1.0196 0.10003 0.09311 0.0039 0.2175 1.0000
15.750 1.0444 0.10240 0.09566 0.0034 0.2083 1.0000
16.000 1.0796 0.09985 0.09319 0.0045 0.2069 1.0000
16.500 1.0802 0.10623 0.09973 0.0023 0.1937 1.0000
17.000 1.0799 0.11294 0.10659 -0.0002 0.1809 1.0000
17.250 1.0469 0.12223 0.11595 -0.0039 0.1704 1.0000
17.500 1.0803 0.11965 0.11345 -0.0029 0.1682 1.0000
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Polar data table (+)
Polar graphs
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