EPPLER 543 AIRFOIL (e543-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 543 AIRFOIL (e543-il) Reynolds number: 1,000,000 Max Cl/Cd: 98.13 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e543-il-1000000-n5.txt Download as CSV file: xf-e543-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 543 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
------ -------- --------- --------- -------- -------- --------
-16.500 -0.7634 0.08611 0.08383 -0.0596 1.0000 0.0025
-16.250 -0.8156 0.07156 0.06897 -0.0681 1.0000 0.0024
-16.000 -0.8302 0.06561 0.06290 -0.0710 1.0000 0.0024
-15.750 -0.8549 0.05891 0.05599 -0.0734 1.0000 0.0024
-15.500 -0.8836 0.05259 0.04942 -0.0744 1.0000 0.0024
-15.250 -0.8828 0.05018 0.04695 -0.0745 1.0000 0.0024
-15.000 -0.8886 0.04722 0.04387 -0.0741 1.0000 0.0024
-14.750 -0.8959 0.04431 0.04083 -0.0733 1.0000 0.0025
-14.500 -0.9017 0.04171 0.03809 -0.0721 1.0000 0.0025
-14.250 -0.9022 0.03974 0.03603 -0.0709 1.0000 0.0025
-14.000 -0.8992 0.03814 0.03434 -0.0696 1.0000 0.0026
-13.750 -0.9008 0.03616 0.03224 -0.0679 1.0000 0.0026
-13.500 -0.9015 0.03407 0.02999 -0.0663 0.9998 0.0026
-13.250 -0.8852 0.03209 0.02787 -0.0676 0.9982 0.0026
-13.000 -0.8713 0.03067 0.02636 -0.0675 0.9920 0.0027
-12.750 -0.8620 0.02956 0.02519 -0.0661 0.9702 0.0027
-12.500 -0.8290 0.02761 0.02306 -0.0703 0.9551 0.0028
-12.250 -0.7878 0.02557 0.02081 -0.0763 0.9436 0.0028
-12.000 -0.7338 0.02425 0.01936 -0.0840 0.9331 0.0029
-11.750 -0.6807 0.02271 0.01760 -0.0917 0.9125 0.0029
-11.500 -0.6510 0.02184 0.01650 -0.0939 0.8801 0.0030
-11.250 -0.6355 0.02120 0.01569 -0.0929 0.8571 0.0031
-11.000 -0.6216 0.02056 0.01491 -0.0914 0.8396 0.0031
-10.750 -0.6069 0.01999 0.01423 -0.0900 0.8250 0.0031
-10.500 -0.5946 0.01924 0.01335 -0.0882 0.8116 0.0031
-10.250 -0.5782 0.01876 0.01279 -0.0869 0.7994 0.0032
-10.000 -0.5621 0.01825 0.01219 -0.0856 0.7890 0.0032
-9.750 -0.5471 0.01770 0.01153 -0.0841 0.7788 0.0032
-9.500 -0.5306 0.01719 0.01096 -0.0828 0.7698 0.0033
-9.250 -0.5135 0.01676 0.01046 -0.0816 0.7618 0.0033
-9.000 -0.4962 0.01632 0.00997 -0.0804 0.7536 0.0034
-8.750 -0.4820 0.01572 0.00928 -0.0786 0.7459 0.0036
-8.500 -0.4641 0.01533 0.00885 -0.0774 0.7382 0.0037
-8.250 -0.4471 0.01494 0.00840 -0.0761 0.7307 0.0039
-8.000 -0.4291 0.01456 0.00798 -0.0748 0.7238 0.0041
-7.750 -0.4118 0.01419 0.00756 -0.0735 0.7170 0.0042
-7.500 -0.3934 0.01386 0.00719 -0.0723 0.7113 0.0043
-7.250 -0.3759 0.01349 0.00678 -0.0709 0.7052 0.0047
-6.750 -0.3404 0.01286 0.00605 -0.0681 0.6935 0.0049
-6.500 -0.3241 0.01250 0.00566 -0.0665 0.6876 0.0056
-6.250 -0.3078 0.01218 0.00531 -0.0648 0.6822 0.0067
-6.000 -0.2910 0.01187 0.00498 -0.0631 0.6773 0.0076
-5.750 -0.2761 0.01158 0.00467 -0.0611 0.6722 0.0098
-5.250 -0.2485 0.01113 0.00421 -0.0564 0.6631 0.0183
-5.000 -0.2301 0.01089 0.00399 -0.0549 0.6582 0.0256
-4.750 -0.2119 0.01065 0.00378 -0.0534 0.6535 0.0379
-4.500 -0.1938 0.01036 0.00356 -0.0520 0.6493 0.0571
-4.250 -0.1752 0.01003 0.00334 -0.0506 0.6454 0.0859
-4.000 -0.1594 0.00956 0.00309 -0.0488 0.6413 0.1402
-3.750 -0.1445 0.00902 0.00281 -0.0469 0.6374 0.2140
-3.500 -0.1303 0.00832 0.00248 -0.0450 0.6338 0.3149
-3.250 -0.1169 0.00738 0.00205 -0.0431 0.6301 0.4507
-3.000 -0.1027 0.00634 0.00165 -0.0413 0.6261 0.6227
-2.750 -0.0757 0.00632 0.00169 -0.0413 0.6224 0.6645
-2.500 -0.0475 0.00639 0.00173 -0.0414 0.6190 0.6816
-2.250 -0.0187 0.00647 0.00181 -0.0417 0.6161 0.6932
-2.000 0.0099 0.00658 0.00191 -0.0420 0.6126 0.7021
-1.750 0.0386 0.00672 0.00201 -0.0422 0.6089 0.7093
-1.500 0.0671 0.00676 0.00198 -0.0425 0.6055 0.7110
-1.250 0.0957 0.00678 0.00194 -0.0429 0.6025 0.7116
-1.000 0.1247 0.00676 0.00191 -0.0433 0.5994 0.7124
-0.750 0.1534 0.00676 0.00188 -0.0437 0.5961 0.7132
-0.500 0.1820 0.00677 0.00187 -0.0441 0.5928 0.7140
-0.250 0.2103 0.00679 0.00186 -0.0444 0.5895 0.7146
0.000 0.2388 0.00682 0.00185 -0.0447 0.5864 0.7153
0.250 0.2676 0.00683 0.00186 -0.0452 0.5834 0.7159
0.500 0.2962 0.00685 0.00186 -0.0455 0.5797 0.7166
0.750 0.3245 0.00688 0.00187 -0.0459 0.5758 0.7172
1.000 0.3523 0.00693 0.00188 -0.0461 0.5715 0.7179
1.250 0.3810 0.00694 0.00190 -0.0465 0.5673 0.7188
1.500 0.4093 0.00698 0.00193 -0.0468 0.5626 0.7196
1.750 0.4371 0.00703 0.00195 -0.0470 0.5579 0.7204
2.000 0.4651 0.00707 0.00198 -0.0473 0.5537 0.7211
2.250 0.4934 0.00710 0.00202 -0.0476 0.5490 0.7218
2.500 0.5211 0.00715 0.00206 -0.0478 0.5436 0.7225
2.750 0.5486 0.00720 0.00210 -0.0480 0.5385 0.7232
3.000 0.5767 0.00724 0.00214 -0.0483 0.5329 0.7239
3.250 0.6038 0.00731 0.00220 -0.0484 0.5264 0.7245
3.500 0.6313 0.00737 0.00225 -0.0486 0.5199 0.7252
3.750 0.6582 0.00745 0.00231 -0.0487 0.5119 0.7258
4.000 0.6850 0.00753 0.00239 -0.0488 0.5032 0.7264
4.250 0.7108 0.00764 0.00247 -0.0486 0.4927 0.7270
4.500 0.7370 0.00774 0.00256 -0.0486 0.4811 0.7275
4.750 0.7622 0.00785 0.00265 -0.0483 0.4678 0.7285
5.000 0.7861 0.00802 0.00278 -0.0478 0.4506 0.7295
5.250 0.8086 0.00824 0.00294 -0.0471 0.4296 0.7304
5.500 0.8289 0.00855 0.00314 -0.0460 0.4017 0.7312
5.750 0.8482 0.00889 0.00338 -0.0447 0.3727 0.7320
6.000 0.8661 0.00928 0.00364 -0.0431 0.3432 0.7328
6.250 0.8838 0.00966 0.00392 -0.0415 0.3167 0.7337
6.500 0.8999 0.01006 0.00422 -0.0397 0.2902 0.7345
6.750 0.9143 0.01042 0.00448 -0.0374 0.2666 0.7354
7.000 0.9284 0.01076 0.00476 -0.0351 0.2475 0.7363
7.250 0.9414 0.01117 0.00509 -0.0327 0.2265 0.7373
7.500 0.9537 0.01163 0.00546 -0.0302 0.2048 0.7382
7.750 0.9653 0.01212 0.00586 -0.0276 0.1852 0.7392
8.000 0.9764 0.01264 0.00630 -0.0251 0.1649 0.7402
8.250 0.9861 0.01321 0.00679 -0.0224 0.1454 0.7411
8.500 0.9967 0.01378 0.00728 -0.0199 0.1298 0.7420
8.750 1.0085 0.01432 0.00779 -0.0178 0.1176 0.7429
9.000 1.0198 0.01489 0.00834 -0.0156 0.1059 0.7439
9.250 1.0301 0.01553 0.00894 -0.0134 0.0943 0.7452
9.500 1.0345 0.01645 0.00977 -0.0105 0.0768 0.7463
9.750 1.0480 0.01702 0.01037 -0.0090 0.0716 0.7474
10.000 1.0522 0.01807 0.01134 -0.0063 0.0567 0.7485
10.250 1.0635 0.01883 0.01211 -0.0047 0.0507 0.7496
10.500 1.0707 0.01983 0.01307 -0.0027 0.0416 0.7507
10.750 1.0785 0.02085 0.01407 -0.0009 0.0341 0.7518
11.000 1.0876 0.02184 0.01505 0.0007 0.0288 0.7529
11.250 1.0954 0.02294 0.01614 0.0023 0.0232 0.7541
11.500 1.1068 0.02387 0.01710 0.0034 0.0215 0.7552
11.750 1.1153 0.02500 0.01824 0.0048 0.0180 0.7562
12.000 1.1255 0.02606 0.01933 0.0059 0.0159 0.7572
12.250 1.1340 0.02726 0.02055 0.0071 0.0133 0.7582
12.500 1.1433 0.02845 0.02175 0.0081 0.0119 0.7591
12.750 1.1522 0.02968 0.02302 0.0091 0.0103 0.7603
13.000 1.1613 0.03092 0.02431 0.0100 0.0093 0.7617
13.250 1.1704 0.03221 0.02565 0.0108 0.0082 0.7631
13.500 1.1784 0.03361 0.02709 0.0116 0.0072 0.7645
13.750 1.1869 0.03500 0.02854 0.0123 0.0062 0.7658
14.000 1.1944 0.03653 0.03010 0.0130 0.0054 0.7671
14.250 1.2020 0.03809 0.03172 0.0135 0.0047 0.7684
14.500 1.2085 0.03977 0.03345 0.0141 0.0040 0.7697
14.750 1.2157 0.04144 0.03518 0.0145 0.0037 0.7710
15.000 1.2195 0.04347 0.03725 0.0150 0.0026 0.7723
15.250 1.2280 0.04511 0.03896 0.0152 0.0028 0.7735
15.500 1.2319 0.04725 0.04115 0.0155 0.0021 0.7746
16.000 1.2422 0.05138 0.04542 0.0156 0.0018 0.7771
16.250 1.2459 0.05367 0.04779 0.0156 0.0014 0.7787
16.500 1.2508 0.05590 0.05010 0.0155 0.0014 0.7801
16.750 1.2537 0.05841 0.05268 0.0153 0.0012 0.7817
17.000 1.2523 0.06145 0.05580 0.0150 0.0008 0.7832
17.250 1.2552 0.06407 0.05851 0.0145 0.0008 0.7847
17.500 1.2578 0.06679 0.06132 0.0140 0.0008 0.7863
17.750 1.2598 0.06968 0.06429 0.0133 0.0009 0.7878
18.000 1.2589 0.07299 0.06769 0.0124 0.0007 0.7892
18.250 1.2604 0.07604 0.07082 0.0115 0.0007 0.7906
18.750 1.2574 0.08319 0.07818 0.0092 0.0007 0.7940
19.000 1.2537 0.08720 0.08230 0.0077 0.0006 0.7959
19.250 1.2487 0.09150 0.08671 0.0060 0.0005 0.7976
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