EPPLER 546 AIRFOIL (e546-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 546 AIRFOIL (e546-il) Reynolds number: 1,000,000 Max Cl/Cd: 106.64 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e546-il-1000000.txt Download as CSV file: xf-e546-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 546 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
------ -------- --------- --------- -------- -------- --------
-13.250 -0.6530 0.06556 0.06345 -0.0631 1.0000 0.0047
-13.000 -0.6914 0.05742 0.05502 -0.0656 1.0000 0.0048
-12.750 -0.7144 0.05255 0.05001 -0.0660 1.0000 0.0047
-12.250 -0.7597 0.04387 0.04089 -0.0638 1.0000 0.0048
-12.000 -0.7767 0.04061 0.03753 -0.0619 1.0000 0.0045
-11.750 -0.7801 0.03907 0.03572 -0.0598 1.0000 0.0049
-11.500 -0.7901 0.03678 0.03327 -0.0570 1.0000 0.0049
-11.250 -0.8062 0.03400 0.03026 -0.0533 1.0000 0.0050
-11.000 -0.8265 0.03078 0.02675 -0.0485 1.0000 0.0050
-10.750 -0.8127 0.02935 0.02519 -0.0483 0.9988 0.0050
-10.500 -0.7953 0.02612 0.02171 -0.0497 0.9961 0.0053
-10.250 -0.7692 0.02427 0.01967 -0.0511 0.9930 0.0053
-10.000 -0.7443 0.02280 0.01807 -0.0521 0.9878 0.0054
-9.750 -0.7193 0.02156 0.01673 -0.0528 0.9798 0.0055
-9.500 -0.6952 0.02052 0.01560 -0.0532 0.9660 0.0056
-9.250 -0.6612 0.01934 0.01432 -0.0554 0.9584 0.0057
-9.000 -0.6205 0.01827 0.01316 -0.0590 0.9506 0.0058
-8.750 -0.5728 0.01714 0.01194 -0.0641 0.9446 0.0059
-8.500 -0.5240 0.01596 0.01064 -0.0695 0.9340 0.0060
-8.250 -0.4794 0.01505 0.00961 -0.0741 0.9149 0.0062
-8.000 -0.4519 0.01458 0.00900 -0.0749 0.8895 0.0065
-7.750 -0.4357 0.01413 0.00842 -0.0734 0.8669 0.0067
-7.500 -0.4216 0.01374 0.00790 -0.0713 0.8481 0.0068
-7.250 -0.4116 0.01324 0.00730 -0.0685 0.8318 0.0069
-7.000 -0.4072 0.01268 0.00664 -0.0646 0.8168 0.0072
-6.750 -0.3944 0.01226 0.00614 -0.0621 0.8044 0.0075
-6.500 -0.3775 0.01193 0.00574 -0.0604 0.7928 0.0076
-6.000 -0.3406 0.01129 0.00498 -0.0573 0.7714 0.0094
-5.750 -0.3210 0.01098 0.00461 -0.0560 0.7620 0.0113
-5.500 -0.3020 0.01061 0.00422 -0.0546 0.7523 0.0176
-5.250 -0.2829 0.01021 0.00389 -0.0533 0.7432 0.0347
-5.000 -0.2628 0.00985 0.00361 -0.0522 0.7339 0.0590
-4.750 -0.2423 0.00945 0.00334 -0.0512 0.7254 0.0942
-4.500 -0.2232 0.00897 0.00305 -0.0500 0.7170 0.1516
-4.250 -0.2055 0.00824 0.00270 -0.0488 0.7088 0.2470
-4.000 -0.1931 0.00700 0.00212 -0.0470 0.7006 0.4297
-3.750 -0.1751 0.00609 0.00186 -0.0457 0.6926 0.6125
-3.500 -0.1474 0.00615 0.00188 -0.0457 0.6849 0.6334
-3.250 -0.1188 0.00624 0.00190 -0.0459 0.6775 0.6467
-3.000 -0.0909 0.00633 0.00196 -0.0459 0.6697 0.6551
-2.750 -0.0622 0.00642 0.00196 -0.0461 0.6623 0.6610
-2.500 -0.0342 0.00652 0.00204 -0.0462 0.6549 0.6682
-2.250 -0.0057 0.00673 0.00219 -0.0462 0.6480 0.6765
-2.000 0.0222 0.00689 0.00237 -0.0461 0.6407 0.6847
-1.750 0.0504 0.00708 0.00251 -0.0462 0.6337 0.6903
-1.500 0.0791 0.00711 0.00248 -0.0465 0.6267 0.6918
-1.250 0.1072 0.00715 0.00244 -0.0467 0.6199 0.6927
-1.000 0.1360 0.00715 0.00240 -0.0470 0.6133 0.6935
-0.750 0.1640 0.00711 0.00230 -0.0472 0.6065 0.6947
-0.500 0.1924 0.00709 0.00226 -0.0475 0.6003 0.6957
-0.250 0.2207 0.00709 0.00223 -0.0477 0.5937 0.6966
0.000 0.2487 0.00713 0.00222 -0.0479 0.5873 0.6976
0.250 0.2773 0.00713 0.00222 -0.0482 0.5812 0.6986
0.500 0.3054 0.00717 0.00221 -0.0484 0.5749 0.6995
0.750 0.3337 0.00720 0.00222 -0.0487 0.5691 0.7004
1.000 0.3620 0.00722 0.00223 -0.0489 0.5629 0.7013
1.250 0.3897 0.00729 0.00225 -0.0491 0.5567 0.7022
1.500 0.4183 0.00730 0.00226 -0.0494 0.5509 0.7032
1.750 0.4462 0.00735 0.00228 -0.0496 0.5446 0.7041
2.000 0.4741 0.00741 0.00231 -0.0498 0.5383 0.7052
2.250 0.5022 0.00744 0.00234 -0.0500 0.5315 0.7063
2.500 0.5295 0.00753 0.00239 -0.0501 0.5247 0.7073
2.750 0.5580 0.00756 0.00242 -0.0504 0.5188 0.7081
3.000 0.5856 0.00763 0.00247 -0.0505 0.5124 0.7088
3.250 0.6133 0.00770 0.00253 -0.0507 0.5063 0.7095
3.500 0.6410 0.00771 0.00255 -0.0509 0.4995 0.7108
3.750 0.6677 0.00778 0.00261 -0.0509 0.4925 0.7120
4.000 0.6956 0.00781 0.00266 -0.0511 0.4856 0.7130
4.250 0.7221 0.00791 0.00274 -0.0510 0.4779 0.7141
4.500 0.7498 0.00796 0.00283 -0.0512 0.4712 0.7151
4.750 0.7764 0.00806 0.00292 -0.0511 0.4634 0.7162
5.000 0.8035 0.00814 0.00302 -0.0512 0.4557 0.7174
5.250 0.8296 0.00826 0.00313 -0.0511 0.4469 0.7187
5.500 0.8565 0.00835 0.00324 -0.0511 0.4377 0.7200
5.750 0.8823 0.00848 0.00336 -0.0509 0.4271 0.7212
6.000 0.9077 0.00863 0.00349 -0.0507 0.4152 0.7224
6.250 0.9328 0.00880 0.00363 -0.0504 0.4006 0.7235
6.500 0.9576 0.00898 0.00379 -0.0501 0.3857 0.7246
6.750 0.9811 0.00922 0.00398 -0.0495 0.3675 0.7254
7.000 1.0033 0.00948 0.00418 -0.0488 0.3432 0.7270
7.250 1.0236 0.00984 0.00444 -0.0477 0.3155 0.7286
7.500 1.0405 0.01036 0.00480 -0.0460 0.2791 0.7301
7.750 1.0567 0.01090 0.00519 -0.0443 0.2464 0.7315
8.000 1.0742 0.01135 0.00555 -0.0427 0.2214 0.7330
8.250 1.0902 0.01185 0.00595 -0.0409 0.1974 0.7346
8.500 1.1030 0.01236 0.00635 -0.0385 0.1735 0.7363
8.750 1.1143 0.01285 0.00676 -0.0358 0.1522 0.7381
9.000 1.1237 0.01346 0.00725 -0.0329 0.1308 0.7399
9.250 1.1348 0.01403 0.00775 -0.0303 0.1139 0.7413
9.500 1.1445 0.01464 0.00829 -0.0276 0.0967 0.7434
9.750 1.1546 0.01524 0.00885 -0.0251 0.0836 0.7455
10.000 1.1622 0.01596 0.00951 -0.0223 0.0700 0.7476
10.250 1.1708 0.01667 0.01020 -0.0198 0.0596 0.7497
10.500 1.1792 0.01743 0.01093 -0.0174 0.0508 0.7518
10.750 1.1872 0.01825 0.01173 -0.0150 0.0431 0.7540
11.000 1.1953 0.01911 0.01259 -0.0129 0.0369 0.7562
11.750 1.2188 0.02201 0.01554 -0.0072 0.0244 0.7639
12.000 1.2267 0.02308 0.01665 -0.0056 0.0215 0.7668
12.250 1.2336 0.02427 0.01787 -0.0040 0.0192 0.7699
12.500 1.2418 0.02544 0.01909 -0.0027 0.0173 0.7728
12.750 1.2481 0.02677 0.02046 -0.0014 0.0155 0.7762
13.000 1.2558 0.02805 0.02181 -0.0002 0.0143 0.7799
13.250 1.2617 0.02952 0.02333 0.0009 0.0128 0.7836
13.500 1.2680 0.03101 0.02488 0.0018 0.0117 0.7875
13.750 1.2735 0.03261 0.02655 0.0027 0.0103 0.7916
14.000 1.2786 0.03429 0.02830 0.0035 0.0091 0.7965
14.250 1.2824 0.03615 0.03022 0.0043 0.0078 0.8018
14.500 1.2863 0.03805 0.03220 0.0049 0.0068 0.8073
14.750 1.2887 0.04015 0.03437 0.0054 0.0058 0.8141
15.000 1.2897 0.04246 0.03676 0.0059 0.0047 0.8218
15.250 1.2893 0.04494 0.03935 0.0062 0.0037 0.8316
15.500 1.2868 0.04772 0.04224 0.0065 0.0031 0.8438
15.750 1.2856 0.05038 0.04506 0.0068 0.0026 0.8628
16.000 1.2846 0.05279 0.04780 0.0072 0.0026 0.9377
16.250 1.2872 0.05626 0.05137 0.0053 0.0020 1.0000
16.500 1.2796 0.06021 0.05543 0.0046 0.0017 1.0000
16.750 1.2820 0.06305 0.05834 0.0040 0.0019 1.0000
17.000 1.2773 0.06684 0.06223 0.0030 0.0018 1.0000
17.250 1.2760 0.07031 0.06579 0.0021 0.0016 1.0000
17.500 1.2727 0.07413 0.06971 0.0009 0.0016 1.0000
17.750 1.2688 0.07812 0.07380 -0.0005 0.0015 1.0000
18.000 1.2645 0.08227 0.07804 -0.0020 0.0015 1.0000
18.250 1.2594 0.08664 0.08251 -0.0037 0.0014 1.0000
18.500 1.2531 0.09130 0.08728 -0.0056 0.0014 1.0000
18.750 1.2469 0.09604 0.09212 -0.0077 0.0014 1.0000
19.000 1.2382 0.10130 0.09749 -0.0100 0.0014 1.0000
19.250 1.2291 0.10676 0.10306 -0.0126 0.0013 1.0000
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Polar data table (+)
Polar graphs
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