EPPLER 549 AIRFOIL (e549-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 549 AIRFOIL (e549-il) Reynolds number: 1,000,000 Max Cl/Cd: 106.05 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e549-il-1000000-n5.txt Download as CSV file: xf-e549-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 549 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-18.250 -0.7182 0.12180 0.11936 -0.0414 1.0000 0.0024
-18.000 -0.7503 0.11089 0.10831 -0.0467 1.0000 0.0024
-17.750 -0.7910 0.09866 0.09587 -0.0529 1.0000 0.0024
-17.500 -0.8071 0.09163 0.08873 -0.0565 1.0000 0.0024
-17.250 -0.8242 0.08467 0.08164 -0.0600 1.0000 0.0024
-17.000 -0.8462 0.07730 0.07411 -0.0636 1.0000 0.0024
-16.750 -0.8555 0.07233 0.06903 -0.0659 1.0000 0.0024
-16.500 -0.8662 0.06737 0.06395 -0.0679 1.0000 0.0024
-16.250 -0.8772 0.06269 0.05913 -0.0696 1.0000 0.0024
-16.000 -0.8854 0.05862 0.05495 -0.0708 1.0000 0.0024
-15.750 -0.8879 0.05542 0.05166 -0.0716 1.0000 0.0024
-15.500 -0.8960 0.05173 0.04784 -0.0722 1.0000 0.0024
-15.250 -0.8986 0.04883 0.04484 -0.0724 1.0000 0.0024
-15.000 -0.8979 0.04640 0.04232 -0.0725 1.0000 0.0024
-14.750 -0.8976 0.04403 0.03987 -0.0724 1.0000 0.0024
-14.500 -0.8972 0.04179 0.03754 -0.0720 1.0000 0.0024
-14.250 -0.8963 0.03972 0.03538 -0.0715 1.0000 0.0024
-14.000 -0.8952 0.03777 0.03335 -0.0708 1.0000 0.0024
-13.750 -0.8920 0.03605 0.03155 -0.0700 1.0000 0.0024
-13.500 -0.8887 0.03439 0.02982 -0.0690 1.0000 0.0024
-13.250 -0.8758 0.03252 0.02787 -0.0701 0.9991 0.0025
-13.000 -0.8539 0.03104 0.02632 -0.0721 0.9959 0.0024
-12.750 -0.8503 0.02949 0.02471 -0.0706 0.9755 0.0024
-12.500 -0.8183 0.02722 0.02230 -0.0758 0.9546 0.0025
-12.250 -0.7714 0.02499 0.01993 -0.0840 0.9415 0.0027
-12.000 -0.7131 0.02364 0.01847 -0.0929 0.9278 0.0026
-11.500 -0.6515 0.02154 0.01600 -0.0991 0.8648 0.0029
-11.250 -0.6399 0.02079 0.01513 -0.0978 0.8433 0.0030
-11.000 -0.6289 0.02006 0.01427 -0.0964 0.8245 0.0029
-10.750 -0.6164 0.01938 0.01350 -0.0951 0.8111 0.0030
-10.500 -0.6041 0.01870 0.01274 -0.0938 0.7978 0.0032
-10.250 -0.5914 0.01807 0.01202 -0.0924 0.7848 0.0031
-10.000 -0.5785 0.01742 0.01131 -0.0911 0.7734 0.0033
-9.750 -0.5663 0.01675 0.01057 -0.0896 0.7632 0.0035
-9.500 -0.5538 0.01615 0.00989 -0.0880 0.7528 0.0037
-9.250 -0.5416 0.01555 0.00922 -0.0864 0.7429 0.0037
-9.000 -0.5296 0.01501 0.00862 -0.0846 0.7344 0.0039
-8.750 -0.5204 0.01449 0.00804 -0.0823 0.7256 0.0040
-8.500 -0.5124 0.01408 0.00757 -0.0794 0.7176 0.0043
-8.250 -0.4968 0.01371 0.00715 -0.0778 0.7089 0.0047
-8.000 -0.4786 0.01337 0.00677 -0.0765 0.7015 0.0050
-7.750 -0.4592 0.01307 0.00641 -0.0754 0.6941 0.0054
-7.500 -0.4385 0.01278 0.00608 -0.0746 0.6877 0.0058
-7.250 -0.4178 0.01247 0.00574 -0.0737 0.6807 0.0068
-7.000 -0.3959 0.01221 0.00544 -0.0730 0.6740 0.0078
-6.750 -0.3734 0.01194 0.00514 -0.0723 0.6670 0.0093
-6.500 -0.3506 0.01170 0.00487 -0.0717 0.6603 0.0116
-6.250 -0.3271 0.01144 0.00460 -0.0713 0.6539 0.0148
-6.000 -0.3035 0.01118 0.00435 -0.0708 0.6477 0.0201
-5.750 -0.2793 0.01094 0.00411 -0.0705 0.6420 0.0268
-5.500 -0.2557 0.01063 0.00385 -0.0701 0.6355 0.0403
-5.250 -0.2322 0.01033 0.00360 -0.0697 0.6293 0.0585
-5.000 -0.2086 0.00994 0.00333 -0.0693 0.6232 0.0903
-4.750 -0.1857 0.00949 0.00304 -0.0689 0.6174 0.1357
-4.500 -0.1635 0.00890 0.00271 -0.0685 0.6121 0.2072
-4.250 -0.1423 0.00808 0.00228 -0.0681 0.6063 0.3137
-4.000 -0.1207 0.00726 0.00187 -0.0677 0.6002 0.4306
-3.750 -0.0941 0.00701 0.00178 -0.0678 0.5945 0.4888
-3.500 -0.0659 0.00698 0.00176 -0.0680 0.5886 0.5108
-3.250 -0.0376 0.00700 0.00174 -0.0682 0.5829 0.5242
-3.000 -0.0089 0.00701 0.00174 -0.0684 0.5770 0.5363
-2.750 0.0193 0.00707 0.00177 -0.0686 0.5702 0.5485
-2.500 0.0480 0.00713 0.00178 -0.0688 0.5642 0.5560
-2.250 0.0766 0.00714 0.00175 -0.0691 0.5585 0.5580
-2.000 0.1051 0.00716 0.00173 -0.0693 0.5536 0.5593
-1.750 0.1339 0.00718 0.00171 -0.0696 0.5492 0.5605
-1.500 0.1625 0.00720 0.00169 -0.0698 0.5438 0.5619
-1.250 0.1909 0.00724 0.00168 -0.0700 0.5387 0.5633
-1.000 0.2196 0.00726 0.00167 -0.0703 0.5343 0.5647
-0.750 0.2483 0.00729 0.00167 -0.0706 0.5297 0.5659
-0.500 0.2767 0.00733 0.00167 -0.0708 0.5249 0.5671
-0.250 0.3051 0.00737 0.00167 -0.0711 0.5206 0.5682
0.000 0.3339 0.00740 0.00168 -0.0714 0.5167 0.5692
0.250 0.3623 0.00743 0.00169 -0.0716 0.5121 0.5703
0.500 0.3903 0.00747 0.00171 -0.0718 0.5076 0.5717
0.750 0.4187 0.00750 0.00174 -0.0720 0.5037 0.5732
1.000 0.4472 0.00753 0.00177 -0.0723 0.4997 0.5747
1.250 0.4754 0.00758 0.00181 -0.0725 0.4957 0.5760
1.500 0.5033 0.00764 0.00185 -0.0727 0.4920 0.5773
1.750 0.5317 0.00768 0.00190 -0.0729 0.4888 0.5787
2.000 0.5600 0.00772 0.00194 -0.0731 0.4851 0.5800
2.250 0.5880 0.00778 0.00199 -0.0733 0.4809 0.5814
2.500 0.6154 0.00786 0.00206 -0.0734 0.4764 0.5827
2.750 0.6437 0.00791 0.00211 -0.0736 0.4727 0.5839
3.000 0.6717 0.00797 0.00217 -0.0738 0.4687 0.5850
3.250 0.6993 0.00803 0.00225 -0.0739 0.4648 0.5867
3.500 0.7263 0.00811 0.00233 -0.0740 0.4603 0.5884
3.750 0.7541 0.00817 0.00241 -0.0741 0.4555 0.5901
4.000 0.7811 0.00825 0.00250 -0.0741 0.4491 0.5917
4.250 0.8080 0.00835 0.00260 -0.0741 0.4431 0.5933
4.500 0.8349 0.00844 0.00269 -0.0741 0.4361 0.5950
4.750 0.8610 0.00856 0.00281 -0.0740 0.4279 0.5966
5.000 0.8869 0.00870 0.00292 -0.0738 0.4175 0.5982
5.250 0.9130 0.00882 0.00304 -0.0737 0.4090 0.5997
5.750 0.9632 0.00913 0.00333 -0.0731 0.3880 0.6029
6.000 0.9873 0.00931 0.00350 -0.0726 0.3748 0.6049
6.250 1.0099 0.00957 0.00371 -0.0719 0.3577 0.6071
6.500 1.0307 0.00989 0.00395 -0.0708 0.3338 0.6093
6.750 1.0473 0.01039 0.00429 -0.0691 0.2993 0.6115
7.000 1.0650 0.01081 0.00462 -0.0675 0.2799 0.6135
7.250 1.0844 0.01114 0.00492 -0.0663 0.2683 0.6154
7.750 1.1209 0.01167 0.00544 -0.0632 0.2486 0.6195
8.000 1.1363 0.01202 0.00576 -0.0612 0.2327 0.6219
8.250 1.1483 0.01252 0.00617 -0.0586 0.2097 0.6243
8.500 1.1584 0.01309 0.00665 -0.0559 0.1892 0.6268
8.750 1.1697 0.01364 0.00714 -0.0534 0.1733 0.6293
9.000 1.1792 0.01426 0.00769 -0.0507 0.1563 0.6317
9.250 1.1883 0.01490 0.00829 -0.0480 0.1413 0.6342
9.500 1.1978 0.01555 0.00892 -0.0456 0.1286 0.6373
9.750 1.2067 0.01626 0.00960 -0.0432 0.1168 0.6406
10.000 1.2152 0.01704 0.01035 -0.0409 0.1062 0.6441
10.250 1.2228 0.01790 0.01119 -0.0386 0.0961 0.6474
10.500 1.2294 0.01886 0.01213 -0.0363 0.0854 0.6507
10.750 1.2371 0.01983 0.01310 -0.0343 0.0765 0.6544
11.000 1.2443 0.02088 0.01414 -0.0324 0.0688 0.6583
11.250 1.2500 0.02207 0.01533 -0.0304 0.0612 0.6622
11.500 1.2571 0.02324 0.01651 -0.0288 0.0545 0.6660
11.750 1.2636 0.02450 0.01780 -0.0272 0.0491 0.6706
12.000 1.2684 0.02593 0.01923 -0.0257 0.0429 0.6754
12.500 1.2822 0.02867 0.02204 -0.0232 0.0355 0.6853
12.750 1.2856 0.03037 0.02375 -0.0219 0.0302 0.6912
13.250 1.2958 0.03367 0.02715 -0.0199 0.0240 0.7049
13.750 1.3031 0.03744 0.03100 -0.0182 0.0180 0.7208
14.000 1.3081 0.03930 0.03292 -0.0176 0.0166 0.7296
14.250 1.3133 0.04119 0.03488 -0.0171 0.0149 0.7401
14.500 1.3173 0.04324 0.03700 -0.0166 0.0135 0.7514
14.750 1.3220 0.04526 0.03911 -0.0162 0.0124 0.7649
15.000 1.3265 0.04733 0.04128 -0.0159 0.0112 0.7817
15.250 1.3296 0.04957 0.04364 -0.0156 0.0102 0.8046
15.500 1.3327 0.05168 0.04592 -0.0152 0.0095 0.8437
16.000 1.3447 0.05645 0.05107 -0.0164 0.0078 1.0000
16.250 1.3477 0.05903 0.05370 -0.0167 0.0074 1.0000
16.500 1.3511 0.06160 0.05632 -0.0169 0.0067 1.0000
16.750 1.3530 0.06440 0.05917 -0.0173 0.0061 1.0000
17.000 1.3542 0.06734 0.06217 -0.0178 0.0057 1.0000
17.250 1.3564 0.07021 0.06510 -0.0183 0.0053 1.0000
17.500 1.3580 0.07321 0.06817 -0.0190 0.0050 1.0000
17.750 1.3590 0.07634 0.07137 -0.0197 0.0047 1.0000
18.000 1.3591 0.07962 0.07471 -0.0206 0.0043 1.0000
18.250 1.3581 0.08313 0.07828 -0.0216 0.0040 1.0000
18.500 1.3583 0.08652 0.08175 -0.0226 0.0039 1.0000
18.750 1.3574 0.09011 0.08542 -0.0238 0.0034 1.0000
19.000 1.3567 0.09372 0.08910 -0.0250 0.0033 1.0000
19.250 1.3544 0.09764 0.09310 -0.0264 0.0031 1.0000
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Polar data table (+)
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