EPPLER 334 AIRFOIL (e334-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 334 AIRFOIL (e334-il) Reynolds number: 100,000 Max Cl/Cd: 48.58 at α=8.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e334-il-100000-n5.txt Download as CSV file: xf-e334-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3127 0.09614 0.09162 -0.0342 1.0000 0.0427
-8.250 -0.3193 0.09306 0.08863 -0.0368 1.0000 0.0428
-8.000 -0.3340 0.09058 0.08623 -0.0385 1.0000 0.0429
-7.750 -0.3091 0.08630 0.08202 -0.0338 1.0000 0.0448
-7.500 -0.3123 0.08367 0.07950 -0.0335 1.0000 0.0459
-7.250 -0.3220 0.08122 0.07715 -0.0330 1.0000 0.0459
-7.000 -0.3114 0.07727 0.07322 -0.0369 0.9809 0.0485
-6.750 -0.2932 0.07239 0.06813 -0.0464 0.9347 0.0516
-6.500 -0.2718 0.06771 0.06306 -0.0535 0.9019 0.0526
-6.250 -0.2459 0.06221 0.05761 -0.0559 0.8772 0.0539
-6.000 -0.2234 0.05855 0.05379 -0.0581 0.8496 0.0555
-5.750 -0.2057 0.05536 0.05037 -0.0591 0.8234 0.0574
-5.500 -0.1912 0.05471 0.04894 -0.0592 0.7992 0.0635
-5.000 -0.1566 0.04274 0.03631 -0.0569 0.7653 0.0290
-4.750 -0.1401 0.04035 0.03380 -0.0561 0.7481 0.0280
-4.500 -0.1219 0.03775 0.03089 -0.0550 0.7326 0.0266
-4.250 -0.1012 0.03420 0.02664 -0.0528 0.7194 0.0238
-4.000 -0.0803 0.03215 0.02429 -0.0518 0.7057 0.0234
-3.750 -0.0586 0.03017 0.02196 -0.0506 0.6922 0.0230
-3.500 -0.0355 0.02827 0.01967 -0.0494 0.6795 0.0227
-3.250 -0.0112 0.02648 0.01747 -0.0482 0.6676 0.0224
-3.000 0.0143 0.02484 0.01541 -0.0472 0.6567 0.0223
-2.750 0.0405 0.02340 0.01364 -0.0463 0.6450 0.0225
-2.500 0.0674 0.02218 0.01211 -0.0455 0.6341 0.0232
-2.250 0.0935 0.02127 0.01102 -0.0448 0.6242 0.0254
-2.000 0.1196 0.02047 0.01008 -0.0442 0.6134 0.0279
-1.750 0.1451 0.01957 0.00905 -0.0433 0.6040 0.0297
-1.500 0.1692 0.01892 0.00833 -0.0423 0.5948 0.0319
-1.250 0.1930 0.01840 0.00774 -0.0414 0.5855 0.0376
-1.000 0.2171 0.01793 0.00714 -0.0403 0.5774 0.0451
-0.500 0.4152 0.01525 0.00665 -0.0652 0.5526 1.0000
-0.250 0.4380 0.01532 0.00649 -0.0643 0.5453 1.0000
0.000 0.4608 0.01540 0.00641 -0.0635 0.5374 1.0000
0.250 0.4836 0.01550 0.00631 -0.0626 0.5304 1.0000
0.500 0.5065 0.01560 0.00628 -0.0617 0.5234 1.0000
0.750 0.5293 0.01571 0.00626 -0.0609 0.5165 1.0000
1.000 0.5522 0.01585 0.00623 -0.0600 0.5105 1.0000
1.250 0.5749 0.01599 0.00631 -0.0591 0.5036 1.0000
1.500 0.5976 0.01613 0.00632 -0.0582 0.4978 1.0000
1.750 0.6201 0.01630 0.00643 -0.0574 0.4917 1.0000
2.000 0.6426 0.01648 0.00654 -0.0565 0.4856 1.0000
2.250 0.6653 0.01666 0.00661 -0.0556 0.4807 1.0000
2.500 0.6873 0.01687 0.00681 -0.0546 0.4745 1.0000
2.750 0.7095 0.01707 0.00697 -0.0537 0.4690 1.0000
3.000 0.7320 0.01728 0.00708 -0.0527 0.4645 1.0000
3.250 0.7534 0.01753 0.00736 -0.0517 0.4586 1.0000
3.500 0.7752 0.01775 0.00757 -0.0507 0.4532 1.0000
3.750 0.7975 0.01798 0.00774 -0.0497 0.4489 1.0000
4.000 0.8182 0.01827 0.00809 -0.0486 0.4433 1.0000
4.250 0.8393 0.01853 0.00836 -0.0475 0.4382 1.0000
4.500 0.8612 0.01878 0.00855 -0.0465 0.4339 1.0000
4.750 0.8813 0.01909 0.00893 -0.0453 0.4286 1.0000
5.000 0.9017 0.01939 0.00930 -0.0440 0.4234 1.0000
5.250 0.9230 0.01965 0.00954 -0.0429 0.4191 1.0000
5.500 0.9428 0.01999 0.00993 -0.0416 0.4142 1.0000
5.750 0.9619 0.02033 0.01036 -0.0403 0.4089 1.0000
6.000 0.9825 0.02061 0.01067 -0.0391 0.4042 1.0000
6.250 1.0023 0.02094 0.01105 -0.0378 0.3996 1.0000
6.500 1.0200 0.02132 0.01155 -0.0362 0.3940 1.0000
6.750 1.0401 0.02162 0.01189 -0.0349 0.3891 1.0000
7.000 1.0596 0.02196 0.01229 -0.0336 0.3844 1.0000
7.250 1.0762 0.02237 0.01284 -0.0319 0.3783 1.0000
7.500 1.0961 0.02266 0.01316 -0.0306 0.3733 1.0000
7.750 1.1141 0.02305 0.01367 -0.0291 0.3679 1.0000
8.000 1.1312 0.02346 0.01422 -0.0275 0.3617 1.0000
8.250 1.1522 0.02372 0.01449 -0.0264 0.3566 1.0000
8.500 1.1676 0.02423 0.01520 -0.0247 0.3500 1.0000
8.750 1.1863 0.02457 0.01563 -0.0234 0.3439 1.0000
9.000 1.2042 0.02497 0.01613 -0.0220 0.3377 1.0000
9.250 1.2201 0.02542 0.01674 -0.0204 0.3305 1.0000
9.500 1.2388 0.02575 0.01715 -0.0192 0.3243 1.0000
9.750 1.2521 0.02629 0.01789 -0.0173 0.3163 1.0000
10.000 1.2688 0.02665 0.01832 -0.0158 0.3092 1.0000
10.250 1.2804 0.02722 0.01908 -0.0138 0.3007 1.0000
10.500 1.2932 0.02772 0.01970 -0.0119 0.2928 1.0000
10.750 1.3037 0.02829 0.02040 -0.0098 0.2844 1.0000
11.000 1.3105 0.02899 0.02125 -0.0072 0.2759 1.0000
11.250 1.3178 0.02957 0.02188 -0.0047 0.2681 1.0000
11.500 1.3191 0.03062 0.02312 -0.0019 0.2590 1.0000
11.750 1.3221 0.03163 0.02421 0.0004 0.2505 1.0000
12.000 1.3228 0.03291 0.02559 0.0025 0.2416 1.0000
12.250 1.3209 0.03458 0.02739 0.0042 0.2324 1.0000
12.500 1.3190 0.03638 0.02924 0.0056 0.2237 1.0000
12.750 1.3141 0.03868 0.03165 0.0066 0.2146 1.0000
13.000 1.3077 0.04135 0.03442 0.0072 0.2055 1.0000
13.250 1.3020 0.04408 0.03719 0.0076 0.1972 1.0000
13.500 1.2923 0.04752 0.04075 0.0074 0.1883 1.0000
13.750 1.2832 0.05102 0.04432 0.0071 0.1801 1.0000
14.000 1.2746 0.05457 0.04789 0.0067 0.1722 1.0000
14.250 1.2632 0.05870 0.05214 0.0059 0.1642 1.0000
14.500 1.2545 0.06246 0.05590 0.0052 0.1569 1.0000
14.750 1.2429 0.06689 0.06044 0.0041 0.1494 1.0000
15.000 1.2347 0.07090 0.06447 0.0031 0.1425 1.0000
15.250 1.2253 0.07530 0.06896 0.0018 0.1354 1.0000
15.500 1.2172 0.07956 0.07327 0.0005 0.1288 1.0000
15.750 1.2092 0.08394 0.07771 -0.0010 0.1223 1.0000
16.000 1.2023 0.08828 0.08211 -0.0025 0.1161 1.0000
16.250 1.1952 0.09273 0.08662 -0.0041 0.1102 1.0000
16.500 1.1892 0.09707 0.09101 -0.0057 0.1044 1.0000
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Polar data table (+)
Polar graphs
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