EPPLER 544 AIRFOIL (e544-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 544 AIRFOIL (e544-il) Reynolds number: 1,000,000 Max Cl/Cd: 113.53 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e544-il-1000000.txt Download as CSV file: xf-e544-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 544 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.000 -0.4173 0.14679 0.14505 -0.0393 1.0000 0.0084
-14.750 -0.4155 0.14266 0.14094 -0.0408 1.0000 0.0084
-11.250 -0.7157 0.03233 0.02848 -0.0746 0.9630 0.0061
-11.000 -0.6900 0.02843 0.02427 -0.0773 0.9543 0.0050
-10.750 -0.6590 0.02422 0.01951 -0.0801 0.9469 0.0044
-10.500 -0.6116 0.02221 0.01728 -0.0857 0.9398 0.0043
-10.250 -0.5609 0.02066 0.01554 -0.0921 0.9268 0.0043
-10.000 -0.5228 0.01953 0.01421 -0.0958 0.9032 0.0043
-9.750 -0.5025 0.01883 0.01334 -0.0957 0.8785 0.0044
-9.500 -0.4888 0.01816 0.01253 -0.0940 0.8593 0.0044
-9.250 -0.4758 0.01753 0.01179 -0.0923 0.8435 0.0045
-8.750 -0.4493 0.01637 0.01044 -0.0887 0.8171 0.0046
-8.500 -0.4357 0.01582 0.00981 -0.0870 0.8060 0.0048
-8.250 -0.4222 0.01529 0.00919 -0.0851 0.7957 0.0049
-8.000 -0.4081 0.01477 0.00861 -0.0834 0.7861 0.0052
-7.750 -0.3943 0.01427 0.00803 -0.0815 0.7775 0.0055
-7.500 -0.3825 0.01369 0.00737 -0.0793 0.7688 0.0060
-7.250 -0.3682 0.01325 0.00688 -0.0775 0.7611 0.0060
-7.000 -0.3558 0.01278 0.00636 -0.0753 0.7532 0.0064
-6.750 -0.3426 0.01242 0.00595 -0.0732 0.7459 0.0075
-6.500 -0.3346 0.01203 0.00552 -0.0699 0.7385 0.0087
-6.250 -0.3198 0.01178 0.00521 -0.0678 0.7319 0.0100
-6.000 -0.3048 0.01137 0.00482 -0.0659 0.7258 0.0164
-5.750 -0.2886 0.01101 0.00449 -0.0641 0.7198 0.0289
-5.500 -0.2701 0.01069 0.00422 -0.0628 0.7143 0.0437
-5.250 -0.2515 0.01032 0.00394 -0.0615 0.7085 0.0661
-5.000 -0.2332 0.00994 0.00367 -0.0601 0.7030 0.1000
-4.750 -0.2158 0.00943 0.00337 -0.0588 0.6979 0.1520
-4.500 -0.2019 0.00862 0.00297 -0.0570 0.6927 0.2523
-4.250 -0.1930 0.00732 0.00234 -0.0546 0.6878 0.4293
-4.000 -0.1776 0.00638 0.00205 -0.0529 0.6833 0.6092
-3.750 -0.1493 0.00643 0.00211 -0.0531 0.6789 0.6345
-3.500 -0.1207 0.00652 0.00212 -0.0533 0.6743 0.6445
-3.250 -0.0925 0.00660 0.00215 -0.0535 0.6698 0.6508
-3.000 -0.0635 0.00671 0.00222 -0.0538 0.6660 0.6583
-2.750 -0.0348 0.00682 0.00231 -0.0540 0.6620 0.6654
-2.500 -0.0061 0.00703 0.00250 -0.0541 0.6579 0.6729
-2.250 0.0221 0.00724 0.00268 -0.0542 0.6538 0.6805
-2.000 0.0511 0.00741 0.00286 -0.0544 0.6502 0.6852
-1.750 0.0800 0.00741 0.00283 -0.0548 0.6466 0.6867
-1.500 0.1087 0.00741 0.00278 -0.0552 0.6430 0.6877
-1.250 0.1372 0.00743 0.00273 -0.0555 0.6392 0.6888
-1.000 0.1659 0.00744 0.00270 -0.0559 0.6358 0.6898
-0.750 0.1948 0.00743 0.00267 -0.0563 0.6325 0.6907
-0.500 0.2237 0.00743 0.00264 -0.0568 0.6291 0.6915
-0.250 0.2523 0.00745 0.00261 -0.0571 0.6256 0.6921
0.000 0.2808 0.00749 0.00259 -0.0575 0.6218 0.6929
0.250 0.3093 0.00742 0.00253 -0.0579 0.6188 0.6942
0.500 0.3379 0.00739 0.00251 -0.0582 0.6153 0.6952
0.750 0.3663 0.00739 0.00250 -0.0586 0.6114 0.6960
1.000 0.3944 0.00743 0.00250 -0.0588 0.6071 0.6969
1.250 0.4228 0.00744 0.00251 -0.0591 0.6032 0.6977
1.500 0.4512 0.00744 0.00253 -0.0595 0.5995 0.6985
1.750 0.4795 0.00746 0.00254 -0.0598 0.5956 0.6994
2.000 0.5074 0.00751 0.00256 -0.0600 0.5914 0.7003
2.250 0.5356 0.00754 0.00260 -0.0603 0.5874 0.7012
2.500 0.5639 0.00755 0.00263 -0.0606 0.5832 0.7023
2.750 0.5917 0.00758 0.00266 -0.0609 0.5788 0.7034
3.000 0.6192 0.00766 0.00270 -0.0610 0.5742 0.7044
3.250 0.6474 0.00766 0.00275 -0.0613 0.5700 0.7053
3.500 0.6752 0.00769 0.00278 -0.0616 0.5650 0.7062
3.750 0.7022 0.00776 0.00283 -0.0616 0.5596 0.7071
4.000 0.7300 0.00779 0.00289 -0.0618 0.5546 0.7078
4.250 0.7574 0.00783 0.00294 -0.0620 0.5485 0.7084
4.500 0.7836 0.00789 0.00298 -0.0619 0.5426 0.7096
4.750 0.8111 0.00788 0.00303 -0.0621 0.5363 0.7108
5.000 0.8371 0.00794 0.00309 -0.0620 0.5287 0.7119
5.250 0.8637 0.00799 0.00318 -0.0620 0.5206 0.7129
5.500 0.8887 0.00809 0.00327 -0.0617 0.5107 0.7139
5.750 0.9142 0.00818 0.00337 -0.0615 0.4991 0.7151
6.000 0.9388 0.00830 0.00349 -0.0611 0.4855 0.7163
6.250 0.9616 0.00847 0.00363 -0.0603 0.4681 0.7176
6.500 0.9829 0.00870 0.00380 -0.0593 0.4463 0.7188
6.750 1.0013 0.00903 0.00402 -0.0578 0.4185 0.7200
7.000 1.0169 0.00945 0.00431 -0.0558 0.3851 0.7212
7.250 1.0303 0.00993 0.00465 -0.0534 0.3513 0.7223
7.500 1.0414 0.01037 0.00496 -0.0505 0.3234 0.7234
7.750 1.0515 0.01083 0.00530 -0.0475 0.2969 0.7243
8.000 1.0601 0.01137 0.00572 -0.0443 0.2670 0.7258
8.250 1.0705 0.01187 0.00614 -0.0415 0.2432 0.7274
8.500 1.0802 0.01242 0.00660 -0.0387 0.2214 0.7289
8.750 1.0894 0.01300 0.00710 -0.0359 0.2001 0.7304
9.000 1.0984 0.01360 0.00764 -0.0331 0.1808 0.7320
9.250 1.1058 0.01429 0.00826 -0.0302 0.1622 0.7337
9.500 1.1134 0.01502 0.00892 -0.0275 0.1457 0.7354
9.750 1.1214 0.01577 0.00962 -0.0250 0.1304 0.7369
10.000 1.1281 0.01662 0.01041 -0.0225 0.1143 0.7384
10.250 1.1354 0.01751 0.01124 -0.0202 0.1011 0.7397
10.500 1.1429 0.01844 0.01213 -0.0180 0.0895 0.7411
10.750 1.1498 0.01941 0.01308 -0.0159 0.0788 0.7432
11.000 1.1566 0.02045 0.01410 -0.0139 0.0688 0.7451
11.250 1.1641 0.02151 0.01515 -0.0121 0.0601 0.7469
11.500 1.1721 0.02259 0.01623 -0.0105 0.0528 0.7488
11.750 1.1791 0.02378 0.01741 -0.0089 0.0460 0.7507
12.000 1.1847 0.02510 0.01870 -0.0073 0.0390 0.7526
12.250 1.1920 0.02636 0.01997 -0.0059 0.0340 0.7544
12.500 1.1999 0.02763 0.02124 -0.0047 0.0298 0.7561
12.750 1.2063 0.02900 0.02263 -0.0034 0.0258 0.7586
13.000 1.2138 0.03034 0.02401 -0.0023 0.0231 0.7611
13.250 1.2206 0.03179 0.02548 -0.0013 0.0198 0.7635
13.500 1.2275 0.03327 0.02700 -0.0003 0.0180 0.7660
13.750 1.2357 0.03470 0.02848 0.0004 0.0162 0.7685
14.000 1.2419 0.03634 0.03015 0.0012 0.0146 0.7708
14.250 1.2492 0.03792 0.03178 0.0018 0.0129 0.7733
14.500 1.2549 0.03966 0.03357 0.0025 0.0116 0.7763
14.750 1.2612 0.04141 0.03539 0.0030 0.0107 0.7795
15.000 1.2677 0.04318 0.03722 0.0035 0.0096 0.7827
15.250 1.2720 0.04522 0.03931 0.0039 0.0085 0.7861
15.500 1.2779 0.04716 0.04132 0.0042 0.0078 0.7895
15.750 1.2806 0.04942 0.04366 0.0045 0.0067 0.7935
16.000 1.2856 0.05152 0.04584 0.0046 0.0062 0.7980
16.250 1.2897 0.05379 0.04818 0.0046 0.0056 0.8027
16.500 1.2934 0.05612 0.05060 0.0045 0.0054 0.8082
16.750 1.2923 0.05906 0.05364 0.0045 0.0047 0.8146
17.000 1.2947 0.06166 0.05635 0.0042 0.0043 0.8218
17.250 1.2964 0.06436 0.05916 0.0039 0.0040 0.8312
17.500 1.2926 0.06780 0.06271 0.0035 0.0035 0.8424
17.750 1.2903 0.07108 0.06614 0.0030 0.0034 0.8590
18.000 1.2874 0.07388 0.06926 0.0032 0.0033 0.9315
18.250 1.2916 0.07767 0.07321 0.0006 0.0032 1.0000
18.500 1.2901 0.08127 0.07689 -0.0005 0.0029 1.0000
18.750 1.2887 0.08492 0.08063 -0.0018 0.0028 1.0000
19.000 1.2842 0.08911 0.08490 -0.0032 0.0027 1.0000
19.250 1.2798 0.09334 0.08923 -0.0049 0.0026 1.0000
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Polar data table (+)
Polar graphs
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