EPPLER 548 AIRFOIL (e548-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 548 AIRFOIL (e548-il) Reynolds number: 1,000,000 Max Cl/Cd: 117.21 at α=8° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e548-il-1000000.txt Download as CSV file: xf-e548-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 548 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
------ -------- --------- --------- -------- -------- --------
-12.750 -0.7643 0.04711 0.04406 -0.0594 1.0000 0.0060
-12.500 -0.7638 0.04539 0.04223 -0.0585 1.0000 0.0060
-12.250 -0.7683 0.04247 0.03931 -0.0573 1.0000 0.0056
-12.000 -0.7870 0.03874 0.03537 -0.0551 1.0000 0.0055
-11.750 -0.7970 0.03598 0.03241 -0.0528 1.0000 0.0054
-11.500 -0.8137 0.03220 0.02831 -0.0494 1.0000 0.0051
-11.250 -0.8159 0.02992 0.02581 -0.0467 1.0000 0.0050
-11.000 -0.8141 0.02741 0.02304 -0.0444 0.9998 0.0049
-10.750 -0.7911 0.02491 0.02027 -0.0455 0.9907 0.0048
-10.500 -0.7313 0.02271 0.01786 -0.0538 0.9419 0.0047
-10.250 -0.6249 0.02031 0.01509 -0.0718 0.8918 0.0048
-10.000 -0.6074 0.01977 0.01419 -0.0708 0.8192 0.0048
-9.750 -0.5964 0.01911 0.01333 -0.0686 0.7835 0.0049
-9.500 -0.5836 0.01851 0.01258 -0.0667 0.7580 0.0050
-9.250 -0.5702 0.01790 0.01184 -0.0649 0.7370 0.0050
-9.000 -0.5568 0.01727 0.01109 -0.0631 0.7187 0.0053
-8.750 -0.5429 0.01670 0.01041 -0.0613 0.7027 0.0054
-8.500 -0.5285 0.01617 0.00979 -0.0595 0.6881 0.0055
-8.250 -0.5143 0.01566 0.00919 -0.0577 0.6742 0.0055
-8.000 -0.5002 0.01514 0.00859 -0.0559 0.6615 0.0056
-7.750 -0.4883 0.01455 0.00791 -0.0536 0.6507 0.0060
-7.500 -0.4787 0.01397 0.00728 -0.0509 0.6403 0.0068
-7.250 -0.4666 0.01363 0.00688 -0.0484 0.6306 0.0069
-7.000 -0.4513 0.01337 0.00655 -0.0464 0.6217 0.0075
-6.750 -0.4327 0.01308 0.00620 -0.0449 0.6129 0.0079
-6.500 -0.4163 0.01265 0.00573 -0.0431 0.6051 0.0091
-6.250 -0.3960 0.01238 0.00541 -0.0420 0.5971 0.0099
-6.000 -0.3765 0.01205 0.00504 -0.0407 0.5897 0.0118
-5.750 -0.3558 0.01173 0.00471 -0.0396 0.5824 0.0155
-5.500 -0.3351 0.01144 0.00441 -0.0385 0.5753 0.0229
-5.250 -0.3137 0.01109 0.00413 -0.0376 0.5695 0.0366
-5.000 -0.2920 0.01077 0.00388 -0.0368 0.5634 0.0554
-4.750 -0.2707 0.01042 0.00363 -0.0359 0.5578 0.0840
-4.500 -0.2498 0.00994 0.00335 -0.0351 0.5530 0.1317
-4.250 -0.2312 0.00927 0.00301 -0.0340 0.5480 0.2146
-4.000 -0.2156 0.00828 0.00254 -0.0326 0.5432 0.3557
-3.750 -0.2010 0.00690 0.00199 -0.0311 0.5392 0.5669
-3.500 -0.1735 0.00685 0.00204 -0.0311 0.5346 0.6228
-3.250 -0.1451 0.00693 0.00209 -0.0312 0.5301 0.6408
-3.000 -0.1166 0.00703 0.00212 -0.0313 0.5255 0.6488
-2.750 -0.0873 0.00708 0.00213 -0.0316 0.5224 0.6555
-2.500 -0.0583 0.00719 0.00222 -0.0318 0.5188 0.6631
-2.250 -0.0294 0.00735 0.00231 -0.0320 0.5152 0.6705
-2.000 -0.0011 0.00751 0.00248 -0.0320 0.5115 0.6781
-1.750 0.0279 0.00781 0.00272 -0.0320 0.5081 0.6860
-1.500 0.0566 0.00780 0.00273 -0.0322 0.5053 0.6905
-1.250 0.0857 0.00780 0.00271 -0.0325 0.5022 0.6916
-1.000 0.1146 0.00781 0.00268 -0.0329 0.4993 0.6925
-0.750 0.1434 0.00784 0.00266 -0.0332 0.4963 0.6935
-0.500 0.1720 0.00790 0.00266 -0.0334 0.4929 0.6946
-0.250 0.2012 0.00790 0.00265 -0.0338 0.4908 0.6956
0.000 0.2304 0.00790 0.00263 -0.0342 0.4883 0.6966
0.250 0.2595 0.00791 0.00262 -0.0346 0.4858 0.6975
0.500 0.2884 0.00793 0.00261 -0.0349 0.4833 0.6984
0.750 0.3171 0.00798 0.00262 -0.0352 0.4806 0.6994
1.000 0.3455 0.00807 0.00265 -0.0355 0.4774 0.7004
1.250 0.3746 0.00809 0.00267 -0.0359 0.4755 0.7012
1.500 0.4037 0.00811 0.00268 -0.0363 0.4735 0.7019
1.750 0.4328 0.00814 0.00270 -0.0367 0.4712 0.7025
2.000 0.4615 0.00812 0.00268 -0.0370 0.4688 0.7037
2.250 0.4900 0.00813 0.00269 -0.0373 0.4663 0.7048
2.500 0.5183 0.00818 0.00273 -0.0376 0.4636 0.7058
2.750 0.5466 0.00827 0.00280 -0.0379 0.4606 0.7067
3.000 0.5754 0.00828 0.00284 -0.0382 0.4587 0.7076
3.250 0.6041 0.00830 0.00288 -0.0385 0.4561 0.7087
3.500 0.6327 0.00833 0.00293 -0.0388 0.4532 0.7098
3.750 0.6610 0.00838 0.00298 -0.0391 0.4501 0.7109
4.000 0.6889 0.00847 0.00306 -0.0393 0.4468 0.7120
4.250 0.7171 0.00854 0.00314 -0.0396 0.4439 0.7131
4.500 0.7457 0.00856 0.00320 -0.0399 0.4413 0.7141
4.750 0.7742 0.00859 0.00326 -0.0402 0.4380 0.7152
5.000 0.8022 0.00865 0.00332 -0.0405 0.4344 0.7162
5.250 0.8296 0.00875 0.00341 -0.0406 0.4305 0.7172
5.500 0.8577 0.00882 0.00350 -0.0409 0.4272 0.7181
5.750 0.8861 0.00885 0.00358 -0.0412 0.4237 0.7189
6.000 0.9138 0.00888 0.00364 -0.0414 0.4194 0.7201
6.250 0.9406 0.00896 0.00372 -0.0414 0.4147 0.7216
6.500 0.9683 0.00901 0.00382 -0.0416 0.4104 0.7229
6.750 0.9960 0.00905 0.00392 -0.0418 0.4052 0.7243
7.000 1.0223 0.00916 0.00403 -0.0418 0.3991 0.7257
7.250 1.0497 0.00923 0.00415 -0.0419 0.3934 0.7271
7.500 1.0762 0.00933 0.00428 -0.0419 0.3859 0.7285
7.750 1.1026 0.00945 0.00442 -0.0419 0.3777 0.7299
8.000 1.1276 0.00962 0.00458 -0.0417 0.3666 0.7313
8.250 1.1521 0.00983 0.00476 -0.0414 0.3523 0.7327
8.500 1.1755 0.01009 0.00498 -0.0409 0.3343 0.7340
8.750 1.1963 0.01048 0.00529 -0.0400 0.3109 0.7351
9.000 1.2144 0.01098 0.00568 -0.0387 0.2839 0.7368
9.250 1.2299 0.01156 0.00614 -0.0370 0.2560 0.7387
9.500 1.2441 0.01218 0.00665 -0.0350 0.2313 0.7406
9.750 1.2584 0.01274 0.00714 -0.0331 0.2097 0.7424
10.000 1.2696 0.01334 0.00767 -0.0306 0.1900 0.7444
10.500 1.2825 0.01457 0.00878 -0.0241 0.1568 0.7488
10.750 1.2878 0.01529 0.00944 -0.0208 0.1420 0.7508
11.000 1.2910 0.01610 0.01020 -0.0175 0.1276 0.7529
11.250 1.2930 0.01698 0.01106 -0.0143 0.1154 0.7558
11.750 1.2941 0.01920 0.01326 -0.0084 0.0946 0.7613
12.000 1.2948 0.02053 0.01460 -0.0061 0.0861 0.7641
12.250 1.2944 0.02209 0.01616 -0.0041 0.0786 0.7668
12.500 1.2924 0.02391 0.01797 -0.0022 0.0707 0.7698
12.750 1.2916 0.02577 0.01988 -0.0007 0.0635 0.7734
13.000 1.2903 0.02780 0.02193 0.0005 0.0578 0.7769
13.250 1.2907 0.02981 0.02398 0.0015 0.0533 0.7807
13.500 1.2879 0.03216 0.02634 0.0024 0.0474 0.7841
13.750 1.2843 0.03462 0.02883 0.0033 0.0428 0.7884
14.000 1.2849 0.03678 0.03105 0.0038 0.0394 0.7932
14.250 1.2813 0.03939 0.03369 0.0044 0.0354 0.7982
14.500 1.2803 0.04183 0.03618 0.0047 0.0321 0.8036
14.750 1.2784 0.04441 0.03883 0.0050 0.0294 0.8102
15.000 1.2771 0.04706 0.04152 0.0051 0.0265 0.8170
15.250 1.2766 0.04965 0.04420 0.0051 0.0247 0.8257
15.500 1.2764 0.05227 0.04690 0.0050 0.0225 0.8361
16.000 1.2748 0.05754 0.05240 0.0050 0.0189 0.8775
16.500 1.2832 0.06330 0.05847 0.0022 0.0159 1.0000
16.750 1.2832 0.06633 0.06155 0.0015 0.0149 1.0000
17.000 1.2839 0.06933 0.06459 0.0008 0.0134 1.0000
17.250 1.2844 0.07241 0.06772 -0.0001 0.0127 1.0000
17.500 1.2833 0.07573 0.07109 -0.0010 0.0117 1.0000
17.750 1.2838 0.07894 0.07436 -0.0020 0.0108 1.0000
18.000 1.2846 0.08214 0.07761 -0.0031 0.0101 1.0000
18.250 1.2823 0.08580 0.08132 -0.0044 0.0093 1.0000
18.500 1.2812 0.08937 0.08496 -0.0057 0.0086 1.0000
18.750 1.2812 0.09284 0.08848 -0.0070 0.0081 1.0000
19.000 1.2786 0.09675 0.09245 -0.0086 0.0074 1.0000
19.250 1.2759 0.10070 0.09647 -0.0102 0.0070 1.0000
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Polar data table (+)
Polar graphs
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