EPPLER 545 AIRFOIL (e545-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 545 AIRFOIL (e545-il) Reynolds number: 500,000 Max Cl/Cd: 90.97 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e545-il-500000.txt Download as CSV file: xf-e545-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 545 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.500 -0.4763 0.08794 0.08565 -0.0650 1.0000 0.0201
-12.250 -0.5203 0.07697 0.07453 -0.0712 1.0000 0.0197
-12.000 -0.5517 0.07052 0.06797 -0.0735 1.0000 0.0197
-11.750 -0.5786 0.06560 0.06294 -0.0741 1.0000 0.0197
-11.500 -0.6017 0.06175 0.05898 -0.0736 1.0000 0.0197
-11.250 -0.6237 0.05858 0.05572 -0.0721 1.0000 0.0197
-11.000 -0.6459 0.05620 0.05327 -0.0693 1.0000 0.0198
-10.750 -0.6609 0.02503 0.02060 -0.0733 0.9840 0.0110
-10.500 -0.7061 0.03462 0.02989 -0.0710 0.9821 0.0111
-10.250 -0.6836 0.03177 0.02683 -0.0715 0.9739 0.0101
-10.000 -0.6590 0.02742 0.02178 -0.0712 0.9690 0.0086
-9.750 -0.6320 0.02612 0.02032 -0.0723 0.9597 0.0085
-9.500 -0.5970 0.02466 0.01873 -0.0742 0.9552 0.0085
-9.250 -0.5612 0.02326 0.01723 -0.0760 0.9491 0.0085
-9.000 -0.5237 0.02172 0.01563 -0.0782 0.9436 0.0086
-8.750 -0.4811 0.02046 0.01432 -0.0825 0.9373 0.0087
-8.500 -0.4405 0.01918 0.01299 -0.0869 0.9261 0.0090
-8.250 -0.4040 0.01813 0.01186 -0.0904 0.9107 0.0092
-8.000 -0.3792 0.01723 0.01083 -0.0915 0.8916 0.0099
-7.750 -0.3627 0.01654 0.01001 -0.0906 0.8734 0.0106
-7.500 -0.3544 0.01574 0.00912 -0.0883 0.8567 0.0114
-7.250 -0.3443 0.01517 0.00845 -0.0861 0.8424 0.0122
-7.000 -0.3398 0.01457 0.00776 -0.0827 0.8295 0.0141
-6.750 -0.3321 0.01410 0.00722 -0.0797 0.8177 0.0169
-6.500 -0.3225 0.01349 0.00661 -0.0770 0.8075 0.0265
-6.250 -0.3109 0.01288 0.00608 -0.0747 0.7976 0.0483
-6.000 -0.2959 0.01236 0.00566 -0.0730 0.7886 0.0754
-5.750 -0.2816 0.01173 0.00521 -0.0713 0.7796 0.1211
-5.500 -0.2703 0.01078 0.00464 -0.0694 0.7713 0.2091
-5.250 -0.2657 0.00906 0.00370 -0.0669 0.7627 0.3945
-5.000 -0.2485 0.00841 0.00362 -0.0655 0.7552 0.5565
-4.750 -0.2213 0.00859 0.00379 -0.0653 0.7473 0.5834
-4.500 -0.1934 0.00882 0.00391 -0.0651 0.7398 0.5977
-4.250 -0.1657 0.00900 0.00396 -0.0651 0.7323 0.6079
-4.000 -0.1377 0.00918 0.00413 -0.0649 0.7251 0.6149
-3.750 -0.1094 0.00942 0.00426 -0.0649 0.7190 0.6228
-3.500 -0.0817 0.00960 0.00444 -0.0648 0.7122 0.6300
-3.250 -0.0535 0.01002 0.00482 -0.0645 0.7055 0.6390
-3.000 -0.0258 0.01035 0.00512 -0.0641 0.6989 0.6476
-2.750 0.0020 0.01051 0.00528 -0.0640 0.6922 0.6514
-2.500 0.0301 0.01051 0.00518 -0.0641 0.6864 0.6533
-2.250 0.0582 0.01049 0.00509 -0.0644 0.6810 0.6552
-2.000 0.0862 0.01042 0.00497 -0.0647 0.6751 0.6568
-1.750 0.1143 0.01039 0.00484 -0.0649 0.6694 0.6584
-1.500 0.1426 0.01037 0.00474 -0.0653 0.6641 0.6600
-1.250 0.1708 0.01032 0.00464 -0.0656 0.6587 0.6612
-1.000 0.1991 0.01029 0.00454 -0.0659 0.6534 0.6621
-0.750 0.2272 0.01021 0.00438 -0.0662 0.6484 0.6634
-0.500 0.2549 0.01014 0.00431 -0.0664 0.6433 0.6648
-0.250 0.2829 0.01010 0.00426 -0.0666 0.6381 0.6659
0.000 0.3110 0.01009 0.00421 -0.0668 0.6334 0.6670
0.250 0.3393 0.01011 0.00419 -0.0671 0.6286 0.6681
0.500 0.3671 0.01008 0.00417 -0.0673 0.6237 0.6692
0.750 0.3951 0.01007 0.00415 -0.0675 0.6188 0.6704
1.000 0.4231 0.01010 0.00412 -0.0678 0.6136 0.6717
1.250 0.4510 0.01011 0.00412 -0.0680 0.6087 0.6731
1.500 0.4788 0.01011 0.00413 -0.0682 0.6037 0.6747
1.750 0.5066 0.01013 0.00412 -0.0684 0.5986 0.6761
2.000 0.5348 0.01019 0.00412 -0.0687 0.5936 0.6774
2.250 0.5621 0.01017 0.00413 -0.0688 0.5880 0.6787
2.500 0.5894 0.01019 0.00414 -0.0689 0.5818 0.6798
2.750 0.6169 0.01026 0.00415 -0.0691 0.5755 0.6808
3.000 0.6435 0.01018 0.00413 -0.0690 0.5692 0.6823
3.250 0.6703 0.01018 0.00414 -0.0690 0.5630 0.6836
3.500 0.6972 0.01024 0.00420 -0.0690 0.5574 0.6849
3.750 0.7241 0.01024 0.00427 -0.0690 0.5516 0.6863
4.000 0.7507 0.01029 0.00434 -0.0690 0.5457 0.6878
4.250 0.7773 0.01038 0.00442 -0.0690 0.5402 0.6895
4.500 0.8040 0.01041 0.00452 -0.0689 0.5344 0.6913
4.750 0.8301 0.01047 0.00460 -0.0688 0.5275 0.6930
5.000 0.8561 0.01055 0.00469 -0.0687 0.5209 0.6946
5.250 0.8822 0.01060 0.00479 -0.0685 0.5136 0.6962
5.500 0.9075 0.01072 0.00490 -0.0683 0.5065 0.6978
5.750 0.9333 0.01078 0.00502 -0.0681 0.4984 0.6991
6.000 0.9569 0.01085 0.00510 -0.0675 0.4888 0.7010
6.250 0.9803 0.01092 0.00523 -0.0668 0.4756 0.7028
6.500 1.0020 0.01105 0.00537 -0.0659 0.4593 0.7046
6.750 1.0225 0.01124 0.00554 -0.0647 0.4409 0.7065
7.000 1.0409 0.01149 0.00575 -0.0631 0.4194 0.7085
7.250 1.0571 0.01182 0.00601 -0.0612 0.3919 0.7107
7.500 1.0690 0.01227 0.00634 -0.0585 0.3612 0.7131
7.750 1.0760 0.01279 0.00673 -0.0550 0.3297 0.7154
8.000 1.0829 0.01341 0.00720 -0.0515 0.3016 0.7175
8.250 1.0921 0.01395 0.00768 -0.0486 0.2781 0.7200
8.500 1.1018 0.01453 0.00821 -0.0458 0.2585 0.7224
8.750 1.1113 0.01513 0.00877 -0.0431 0.2409 0.7249
9.000 1.1214 0.01573 0.00935 -0.0406 0.2267 0.7276
9.250 1.1314 0.01637 0.00997 -0.0382 0.2153 0.7305
9.500 1.1402 0.01709 0.01067 -0.0358 0.2051 0.7333
9.750 1.1500 0.01780 0.01139 -0.0336 0.1950 0.7360
10.000 1.1615 0.01843 0.01208 -0.0317 0.1839 0.7393
10.250 1.1719 0.01916 0.01283 -0.0298 0.1667 0.7426
10.500 1.1720 0.02046 0.01394 -0.0269 0.1325 0.7462
10.750 1.1730 0.02183 0.01525 -0.0242 0.1199 0.7501
11.000 1.1766 0.02314 0.01656 -0.0221 0.1108 0.7540
11.250 1.1802 0.02447 0.01793 -0.0200 0.1020 0.7583
11.750 1.1928 0.02703 0.02053 -0.0169 0.0811 0.7678
12.000 1.1975 0.02851 0.02200 -0.0154 0.0714 0.7728
12.250 1.2010 0.03010 0.02361 -0.0140 0.0626 0.7783
12.500 1.2045 0.03177 0.02530 -0.0126 0.0552 0.7847
12.750 1.2081 0.03349 0.02705 -0.0115 0.0494 0.7914
13.000 1.2113 0.03526 0.02888 -0.0103 0.0436 0.7994
13.250 1.2146 0.03711 0.03078 -0.0094 0.0392 0.8088
13.500 1.2167 0.03908 0.03283 -0.0084 0.0354 0.8208
13.750 1.2195 0.04102 0.03487 -0.0075 0.0319 0.8367
14.000 1.2218 0.04288 0.03691 -0.0065 0.0292 0.8649
14.250 1.2280 0.04503 0.03929 -0.0070 0.0264 1.0000
14.500 1.2301 0.04749 0.04177 -0.0069 0.0242 1.0000
14.750 1.2342 0.04980 0.04415 -0.0068 0.0220 1.0000
15.000 1.2358 0.05243 0.04682 -0.0068 0.0202 1.0000
15.250 1.2379 0.05506 0.04949 -0.0069 0.0184 1.0000
15.500 1.2389 0.05788 0.05238 -0.0072 0.0167 1.0000
15.750 1.2397 0.06080 0.05534 -0.0075 0.0153 1.0000
16.000 1.2403 0.06381 0.05845 -0.0079 0.0139 1.0000
16.250 1.2379 0.06726 0.06195 -0.0086 0.0129 1.0000
16.500 1.2372 0.07061 0.06539 -0.0093 0.0118 1.0000
16.750 1.2356 0.07415 0.06901 -0.0101 0.0111 1.0000
17.000 1.2288 0.07848 0.07342 -0.0113 0.0103 1.0000
17.250 1.2272 0.08221 0.07726 -0.0124 0.0096 1.0000
17.500 1.2248 0.08616 0.08128 -0.0138 0.0089 1.0000
17.750 1.2157 0.09118 0.08639 -0.0156 0.0085 1.0000
18.000 1.2106 0.09571 0.09103 -0.0173 0.0083 1.0000
18.250 1.2070 0.10010 0.09555 -0.0191 0.0077 1.0000
18.500 1.2026 0.10469 0.10024 -0.0210 0.0074 1.0000
18.750 1.1968 0.10960 0.10523 -0.0233 0.0071 1.0000
19.000 1.1891 0.11488 0.11060 -0.0258 0.0069 1.0000
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