EPPLER 546 AIRFOIL (e546-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 546 AIRFOIL (e546-il) Reynolds number: 50,000 Max Cl/Cd: 21.64 at α=10.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e546-il-50000-n5.txt Download as CSV file: xf-e546-il-50000-n5.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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.250 -0.4510 0.10805 0.10080 -0.0516 1.0000 0.0367
-12.000 -0.4582 0.10195 0.09474 -0.0545 1.0000 0.0363
-11.750 -0.4708 0.09554 0.08836 -0.0577 1.0000 0.0358
-11.500 -0.4891 0.08921 0.08204 -0.0608 1.0000 0.0353
-11.250 -0.5108 0.08350 0.07629 -0.0630 1.0000 0.0349
-11.000 -0.5331 0.07861 0.07133 -0.0640 1.0000 0.0345
-10.750 -0.5558 0.07436 0.06702 -0.0640 1.0000 0.0342
-10.500 -0.5784 0.07067 0.06322 -0.0629 1.0000 0.0338
-10.250 -0.6001 0.06754 0.05998 -0.0608 1.0000 0.0336
-10.000 -0.6215 0.06488 0.05721 -0.0577 1.0000 0.0334
-9.750 -0.6420 0.06271 0.05493 -0.0536 1.0000 0.0333
-9.500 -0.6598 0.06054 0.05265 -0.0493 1.0000 0.0332
-9.250 -0.6738 0.05835 0.05030 -0.0451 1.0000 0.0332
-9.000 -0.6858 0.05625 0.04803 -0.0408 1.0000 0.0332
-8.750 -0.6955 0.05426 0.04584 -0.0366 1.0000 0.0333
-8.500 -0.7027 0.05235 0.04372 -0.0325 1.0000 0.0335
-8.250 -0.7070 0.05047 0.04161 -0.0287 1.0000 0.0338
-8.000 -0.7085 0.04861 0.03952 -0.0251 1.0000 0.0344
-7.750 -0.7068 0.04686 0.03750 -0.0218 1.0000 0.0352
-7.500 -0.6847 0.04432 0.03437 -0.0217 0.9953 0.0374
-7.250 -0.6504 0.04211 0.03206 -0.0238 0.9886 0.0398
-7.000 -0.6089 0.03998 0.02963 -0.0258 0.9836 0.0428
-6.750 -0.5645 0.03829 0.02781 -0.0278 0.9790 0.0479
-6.500 -0.5152 0.03701 0.02641 -0.0298 0.9752 0.0559
-6.250 -0.4767 0.03577 0.02513 -0.0313 0.9689 0.0677
-6.000 -0.4479 0.03450 0.02388 -0.0321 0.9598 0.0832
-5.750 -0.4284 0.03300 0.02257 -0.0320 0.9488 0.1093
-5.500 -0.4169 0.03112 0.02116 -0.0313 0.9372 0.1618
-5.250 -0.4199 0.02857 0.01970 -0.0290 0.9244 0.2886
-4.750 -0.3700 0.03335 0.02559 -0.0187 0.9056 0.6804
-4.500 -0.3205 0.03600 0.02784 -0.0175 0.9003 0.7239
-4.250 -0.2540 0.03784 0.02923 -0.0199 0.8980 0.7581
-4.000 -0.2061 0.03798 0.02901 -0.0226 0.8919 0.7738
-3.750 -0.1529 0.03760 0.02828 -0.0271 0.8855 0.7800
-3.500 -0.1350 0.03718 0.02764 -0.0264 0.8753 0.7896
-3.250 -0.0887 0.03669 0.02687 -0.0300 0.8679 0.7939
-3.000 -0.0534 0.03621 0.02616 -0.0320 0.8601 0.7994
-2.750 -0.0401 0.03585 0.02565 -0.0304 0.8491 0.8062
-2.500 -0.0051 0.03547 0.02508 -0.0322 0.8402 0.8099
-2.250 0.0269 0.03504 0.02447 -0.0336 0.8323 0.8141
-2.000 0.0264 0.03490 0.02424 -0.0294 0.8202 0.8206
-1.750 0.0664 0.03440 0.02355 -0.0321 0.8141 0.8232
-1.250 0.1163 0.03389 0.02282 -0.0324 0.7967 0.8301
-1.000 0.1155 0.03386 0.02273 -0.0281 0.7854 0.8353
-0.750 0.1353 0.03367 0.02246 -0.0273 0.7771 0.8383
-0.500 0.1608 0.03348 0.02220 -0.0275 0.7689 0.8409
-0.250 0.1811 0.03335 0.02199 -0.0268 0.7607 0.8439
0.000 0.1959 0.03324 0.02183 -0.0252 0.7524 0.8473
0.250 0.1972 0.03323 0.02179 -0.0213 0.7435 0.8513
0.500 0.2183 0.03310 0.02161 -0.0207 0.7360 0.8538
0.750 0.2390 0.03307 0.02155 -0.0201 0.7284 0.8562
1.000 0.2560 0.03305 0.02151 -0.0188 0.7206 0.8587
1.250 0.2742 0.03298 0.02141 -0.0177 0.7138 0.8615
1.500 0.2764 0.03310 0.02153 -0.0141 0.7049 0.8654
1.750 0.2971 0.03289 0.02129 -0.0133 0.6998 0.8680
2.000 0.3030 0.03323 0.02168 -0.0105 0.6899 0.8705
2.250 0.3358 0.03303 0.02146 -0.0117 0.6851 0.8724
2.500 0.3336 0.03348 0.02196 -0.0076 0.6752 0.8764
2.750 0.3582 0.03334 0.02182 -0.0074 0.6699 0.8790
3.000 0.3488 0.03377 0.02228 -0.0023 0.6603 0.8832
3.250 0.3773 0.03374 0.02230 -0.0028 0.6548 0.8851
3.500 0.3876 0.03413 0.02275 -0.0009 0.6466 0.8883
3.750 0.4070 0.03426 0.02292 -0.0001 0.6398 0.8915
4.000 0.4262 0.03436 0.02306 0.0008 0.6337 0.8949
4.250 0.4279 0.03485 0.02361 0.0040 0.6246 0.8990
4.500 0.4666 0.03461 0.02346 0.0022 0.6206 0.9006
4.750 0.4620 0.03554 0.02448 0.0058 0.6095 0.9052
5.000 0.4990 0.03527 0.02429 0.0044 0.6051 0.9077
5.250 0.4891 0.03625 0.02537 0.0087 0.5939 0.9140
5.500 0.5313 0.03594 0.02517 0.0066 0.5893 0.9161
5.750 0.5281 0.03698 0.02631 0.0097 0.5779 0.9218
6.000 0.5705 0.03654 0.02600 0.0078 0.5732 0.9241
6.250 0.5663 0.03768 0.02728 0.0108 0.5614 0.9305
6.500 0.6157 0.03698 0.02673 0.0082 0.5568 0.9324
6.750 0.6143 0.03825 0.02814 0.0106 0.5444 0.9400
7.250 0.6722 0.03845 0.02871 0.0092 0.5270 0.9500
7.500 0.6835 0.03950 0.02993 0.0097 0.5147 0.9581
7.750 0.7413 0.03802 0.02868 0.0069 0.5090 0.9601
8.000 0.7524 0.03906 0.02991 0.0074 0.4954 0.9697
8.250 0.7702 0.03980 0.03087 0.0071 0.4821 0.9808
8.500 0.7866 0.04023 0.03148 0.0074 0.4695 1.0000
8.750 0.8238 0.03892 0.03034 0.0075 0.4602 1.0000
9.000 0.8307 0.03941 0.03094 0.0094 0.4473 1.0000
9.250 0.8363 0.04030 0.03195 0.0108 0.4331 1.0000
9.500 0.8485 0.04087 0.03267 0.0117 0.4184 1.0000
9.750 0.8636 0.04131 0.03326 0.0124 0.4031 1.0000
10.000 0.8810 0.04157 0.03364 0.0131 0.3869 1.0000
10.250 0.9005 0.04161 0.03381 0.0137 0.3697 1.0000
10.500 0.9115 0.04245 0.03474 0.0145 0.3508 1.0000
10.750 0.9186 0.04371 0.03609 0.0152 0.3308 1.0000
11.000 0.9332 0.04425 0.03664 0.0160 0.3099 1.0000
11.250 0.9425 0.04541 0.03778 0.0167 0.2886 1.0000
11.500 0.9483 0.04698 0.03934 0.0174 0.2675 1.0000
11.750 0.9558 0.04837 0.04064 0.0181 0.2470 1.0000
12.000 0.9571 0.05063 0.04287 0.0185 0.2279 1.0000
12.250 0.9580 0.05299 0.04521 0.0188 0.2099 1.0000
12.500 0.9588 0.05544 0.04764 0.0190 0.1933 1.0000
12.750 0.9588 0.05807 0.05024 0.0190 0.1777 1.0000
13.000 0.9587 0.06082 0.05298 0.0189 0.1635 1.0000
13.250 0.9586 0.06368 0.05583 0.0188 0.1505 1.0000
13.500 0.9586 0.06661 0.05876 0.0185 0.1387 1.0000
13.750 0.9590 0.06953 0.06164 0.0181 0.1278 1.0000
14.000 0.9588 0.07271 0.06488 0.0176 0.1178 1.0000
14.250 0.9580 0.07614 0.06843 0.0169 0.1089 1.0000
14.500 0.9591 0.07922 0.07147 0.0162 0.1010 1.0000
14.750 0.9577 0.08296 0.07538 0.0152 0.0938 1.0000
15.000 0.9584 0.08635 0.07880 0.0144 0.0875 1.0000
15.250 0.9556 0.09048 0.08312 0.0131 0.0820 1.0000
15.500 0.9585 0.09360 0.08621 0.0122 0.0769 1.0000
15.750 0.9501 0.09901 0.09193 0.0101 0.0733 1.0000
16.000 0.9473 0.10334 0.09639 0.0084 0.0694 1.0000
16.250 0.9479 0.10709 0.10018 0.0070 0.0660 1.0000
16.500 0.9307 0.11459 0.10798 0.0032 0.0644 1.0000
16.750 0.9102 0.12317 0.11681 -0.0014 0.0634 1.0000
17.000 0.8821 0.13412 0.12793 -0.0075 0.0634 1.0000
17.250 0.8436 0.14902 0.14288 -0.0159 0.0641 1.0000
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