EPPLER 331 AIRFOIL (e331-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 331 AIRFOIL (e331-il) Reynolds number: 100,000 Max Cl/Cd: 46.32 at α=8.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e331-il-100000-n5.txt Download as CSV file: xf-e331-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 331 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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4627 0.09300 0.08850 -0.0085 1.0000 0.0480
-8.500 -0.4657 0.08871 0.08427 -0.0115 1.0000 0.0478
-8.250 -0.4754 0.08437 0.07996 -0.0151 1.0000 0.0494
-8.000 -0.4823 0.08074 0.07635 -0.0159 1.0000 0.0492
-7.750 -0.4912 0.07736 0.07296 -0.0159 1.0000 0.0496
-7.500 -0.5157 0.07527 0.07051 -0.0158 1.0000 0.0516
-7.250 -0.5169 0.07226 0.06733 -0.0145 1.0000 0.0517
-7.000 -0.5013 0.06659 0.06200 -0.0146 1.0000 0.0536
-6.750 -0.4957 0.06346 0.05885 -0.0135 1.0000 0.0547
-6.250 -0.4881 0.05292 0.04777 -0.0093 1.0000 0.0295
-5.750 -0.4666 0.04418 0.03832 -0.0052 0.9706 0.0226
-5.500 -0.4375 0.04048 0.03428 -0.0069 0.9172 0.0219
-5.250 -0.4098 0.03695 0.03027 -0.0073 0.8783 0.0212
-5.000 -0.3874 0.03399 0.02678 -0.0061 0.8448 0.0207
-4.750 -0.3665 0.03142 0.02366 -0.0042 0.8164 0.0203
-4.500 -0.3448 0.02907 0.02080 -0.0023 0.7917 0.0200
-4.250 -0.3212 0.02706 0.01829 -0.0007 0.7698 0.0200
-4.000 -0.2958 0.02531 0.01614 0.0005 0.7492 0.0200
-3.750 -0.2690 0.02376 0.01426 0.0014 0.7304 0.0205
-3.500 -0.2415 0.02239 0.01261 0.0021 0.7127 0.0210
-3.250 -0.2142 0.02126 0.01120 0.0028 0.6960 0.0226
-3.000 -0.1891 0.02042 0.01030 0.0035 0.6802 0.0252
-2.750 -0.1644 0.01959 0.00929 0.0045 0.6654 0.0280
-2.500 -0.1415 0.01878 0.00843 0.0057 0.6513 0.0306
-2.250 -0.1183 0.01818 0.00771 0.0069 0.6380 0.0367
-2.000 -0.0948 0.01755 0.00699 0.0081 0.6255 0.0491
-1.750 0.0074 0.01610 0.00867 -0.0021 0.6078 0.9217
-1.500 0.1287 0.01667 0.00857 -0.0188 0.5875 0.9808
-1.250 0.1684 0.01643 0.00805 -0.0214 0.5746 0.9879
-1.000 0.2007 0.01629 0.00766 -0.0226 0.5633 0.9924
-0.750 0.2333 0.01612 0.00727 -0.0238 0.5522 0.9961
-0.500 0.2658 0.01597 0.00695 -0.0250 0.5411 0.9998
-0.250 0.2891 0.01597 0.00678 -0.0244 0.5320 1.0000
0.000 0.3122 0.01598 0.00666 -0.0237 0.5226 1.0000
0.250 0.3354 0.01601 0.00657 -0.0230 0.5138 1.0000
0.500 0.3586 0.01606 0.00649 -0.0223 0.5056 1.0000
0.750 0.3820 0.01611 0.00646 -0.0216 0.4972 1.0000
1.000 0.4052 0.01618 0.00642 -0.0209 0.4896 1.0000
1.250 0.4288 0.01626 0.00644 -0.0203 0.4816 1.0000
1.500 0.4521 0.01635 0.00644 -0.0196 0.4744 1.0000
1.750 0.4757 0.01645 0.00651 -0.0189 0.4670 1.0000
2.000 0.4992 0.01656 0.00656 -0.0183 0.4599 1.0000
2.250 0.5227 0.01669 0.00664 -0.0176 0.4532 1.0000
2.500 0.5462 0.01683 0.00676 -0.0170 0.4461 1.0000
2.750 0.5696 0.01697 0.00686 -0.0163 0.4401 1.0000
3.000 0.5932 0.01713 0.00705 -0.0157 0.4329 1.0000
3.250 0.6165 0.01729 0.00715 -0.0150 0.4271 1.0000
3.500 0.6399 0.01747 0.00738 -0.0143 0.4204 1.0000
3.750 0.6632 0.01765 0.00759 -0.0136 0.4141 1.0000
4.000 0.6864 0.01785 0.00779 -0.0129 0.4083 1.0000
4.250 0.7096 0.01806 0.00806 -0.0123 0.4016 1.0000
4.500 0.7326 0.01826 0.00824 -0.0115 0.3961 1.0000
4.750 0.7555 0.01851 0.00862 -0.0108 0.3894 1.0000
5.000 0.7783 0.01874 0.00888 -0.0101 0.3834 1.0000
5.250 0.8008 0.01898 0.00917 -0.0093 0.3775 1.0000
5.500 0.8231 0.01926 0.00958 -0.0085 0.3707 1.0000
5.750 0.8455 0.01950 0.00981 -0.0076 0.3652 1.0000
6.000 0.8671 0.01982 0.01030 -0.0067 0.3579 1.0000
6.250 0.8889 0.02008 0.01062 -0.0058 0.3516 1.0000
6.500 0.9101 0.02040 0.01107 -0.0049 0.3447 1.0000
6.750 0.9313 0.02069 0.01146 -0.0039 0.3377 1.0000
7.000 0.9520 0.02101 0.01189 -0.0028 0.3309 1.0000
7.250 0.9723 0.02133 0.01234 -0.0017 0.3232 1.0000
7.500 0.9923 0.02166 0.01278 -0.0005 0.3158 1.0000
7.750 1.0117 0.02198 0.01324 0.0007 0.3077 1.0000
8.000 1.0306 0.02235 0.01376 0.0020 0.2995 1.0000
8.250 1.0491 0.02265 0.01416 0.0034 0.2911 1.0000
8.500 1.0664 0.02307 0.01477 0.0049 0.2814 1.0000
8.750 1.0834 0.02343 0.01523 0.0065 0.2724 1.0000
9.000 1.0993 0.02383 0.01577 0.0082 0.2623 1.0000
9.250 1.1140 0.02431 0.01644 0.0100 0.2515 1.0000
9.500 1.1275 0.02480 0.01705 0.0120 0.2407 1.0000
9.750 1.1395 0.02533 0.01767 0.0142 0.2296 1.0000
10.000 1.1495 0.02593 0.01837 0.0166 0.2179 1.0000
10.250 1.1575 0.02664 0.01921 0.0192 0.2056 1.0000
10.500 1.1628 0.02744 0.02010 0.0221 0.1933 1.0000
10.750 1.1653 0.02832 0.02107 0.0253 0.1817 1.0000
11.000 1.1641 0.02933 0.02213 0.0288 0.1709 1.0000
11.250 1.1571 0.03046 0.02325 0.0329 0.1619 1.0000
11.500 1.1471 0.03171 0.02459 0.0371 0.1532 1.0000
11.750 1.1362 0.03339 0.02632 0.0402 0.1456 1.0000
12.000 1.1262 0.03554 0.02851 0.0421 0.1379 1.0000
12.250 1.1168 0.03810 0.03114 0.0432 0.1304 1.0000
12.500 1.1064 0.04109 0.03416 0.0435 0.1237 1.0000
12.750 1.0970 0.04430 0.03746 0.0435 0.1167 1.0000
13.000 1.0862 0.04784 0.04102 0.0430 0.1109 1.0000
13.250 1.0768 0.05142 0.04469 0.0425 0.1050 1.0000
13.500 1.0661 0.05528 0.04859 0.0416 0.0996 1.0000
13.750 1.0559 0.05916 0.05251 0.0407 0.0946 1.0000
14.000 1.0464 0.06313 0.05657 0.0397 0.0894 1.0000
14.250 1.0367 0.06708 0.06052 0.0386 0.0854 1.0000
14.500 1.0286 0.07109 0.06463 0.0374 0.0805 1.0000
14.750 1.0199 0.07533 0.06893 0.0360 0.0761 1.0000
15.000 1.0132 0.07928 0.07286 0.0347 0.0723 1.0000
15.250 1.0062 0.08359 0.07733 0.0332 0.0680 1.0000
15.500 0.9989 0.08794 0.08171 0.0315 0.0643 1.0000
15.750 0.9935 0.09203 0.08583 0.0301 0.0609 1.0000
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Polar data table (+)
Polar graphs
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