EPPLER 546 AIRFOIL (e546-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 546 AIRFOIL (e546-il) Reynolds number: 200,000 Max Cl/Cd: 61.39 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e546-il-200000-n5.txt Download as CSV file: xf-e546-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.500 -0.5003 0.08964 0.08598 -0.0545 1.0000 0.0102
-12.250 -0.5530 0.07410 0.07020 -0.0636 1.0000 0.0098
-12.000 -0.5944 0.06541 0.06126 -0.0665 1.0000 0.0095
-11.500 -0.6700 0.05257 0.04765 -0.0650 1.0000 0.0091
-11.250 -0.6845 0.04958 0.04447 -0.0631 1.0000 0.0091
-11.000 -0.6969 0.04695 0.04168 -0.0606 1.0000 0.0090
-10.750 -0.7092 0.04454 0.03906 -0.0576 1.0000 0.0090
-10.500 -0.7194 0.04243 0.03679 -0.0543 1.0000 0.0090
-10.250 -0.7303 0.04061 0.03479 -0.0502 1.0000 0.0090
-10.000 -0.7436 0.03911 0.03313 -0.0452 1.0000 0.0090
-9.750 -0.7247 0.03606 0.02967 -0.0465 0.9928 0.0091
-9.500 -0.7028 0.03356 0.02688 -0.0475 0.9845 0.0091
-9.250 -0.6795 0.03149 0.02461 -0.0481 0.9747 0.0093
-9.000 -0.6537 0.02971 0.02265 -0.0489 0.9654 0.0094
-8.750 -0.6230 0.02805 0.02083 -0.0504 0.9584 0.0097
-8.500 -0.5920 0.02657 0.01920 -0.0517 0.9506 0.0100
-8.250 -0.5570 0.02515 0.01764 -0.0536 0.9446 0.0105
-8.000 -0.5233 0.02382 0.01617 -0.0554 0.9367 0.0111
-7.750 -0.4886 0.02259 0.01480 -0.0576 0.9286 0.0116
-7.500 -0.4573 0.02146 0.01364 -0.0595 0.9173 0.0126
-7.250 -0.4249 0.02049 0.01257 -0.0615 0.9056 0.0137
-7.000 -0.3944 0.01960 0.01161 -0.0631 0.8931 0.0159
-6.500 -0.3480 0.01807 0.00987 -0.0632 0.8646 0.0211
-6.250 -0.3314 0.01745 0.00918 -0.0618 0.8504 0.0259
-6.000 -0.3153 0.01686 0.00858 -0.0602 0.8373 0.0340
-5.750 -0.3003 0.01625 0.00801 -0.0585 0.8252 0.0516
-5.250 -0.2754 0.01488 0.00698 -0.0543 0.8021 0.1351
-5.000 -0.2666 0.01398 0.00642 -0.0518 0.7915 0.2154
-4.750 -0.2635 0.01267 0.00570 -0.0485 0.7815 0.3538
-4.500 -0.2592 0.01195 0.00613 -0.0440 0.7714 0.5746
-4.250 -0.2338 0.01223 0.00631 -0.0433 0.7631 0.6304
-4.000 -0.2075 0.01255 0.00651 -0.0426 0.7542 0.6507
-3.750 -0.1807 0.01293 0.00675 -0.0420 0.7462 0.6667
-3.500 -0.1540 0.01348 0.00722 -0.0410 0.7376 0.6823
-3.250 -0.1270 0.01418 0.00785 -0.0399 0.7300 0.6970
-3.000 -0.1004 0.01461 0.00818 -0.0390 0.7218 0.7065
-2.750 -0.0744 0.01453 0.00795 -0.0389 0.7144 0.7107
-2.500 -0.0476 0.01450 0.00782 -0.0387 0.7062 0.7122
-2.250 -0.0205 0.01446 0.00766 -0.0387 0.6992 0.7138
-2.000 0.0060 0.01439 0.00750 -0.0386 0.6914 0.7156
-1.750 0.0329 0.01432 0.00730 -0.0386 0.6846 0.7175
-1.500 0.0592 0.01422 0.00712 -0.0386 0.6768 0.7196
-1.250 0.0861 0.01411 0.00688 -0.0388 0.6700 0.7216
-1.000 0.1128 0.01399 0.00667 -0.0390 0.6630 0.7239
-0.750 0.1398 0.01388 0.00645 -0.0392 0.6559 0.7259
-0.500 0.1669 0.01384 0.00635 -0.0393 0.6494 0.7268
-0.250 0.1938 0.01381 0.00627 -0.0393 0.6424 0.7277
0.000 0.2211 0.01380 0.00619 -0.0393 0.6366 0.7289
0.250 0.2477 0.01379 0.00616 -0.0393 0.6296 0.7303
0.500 0.2748 0.01378 0.00610 -0.0394 0.6232 0.7316
0.750 0.3020 0.01377 0.00604 -0.0395 0.6172 0.7329
1.000 0.3289 0.01375 0.00600 -0.0396 0.6105 0.7342
1.250 0.3563 0.01375 0.00593 -0.0398 0.6049 0.7357
1.500 0.3833 0.01374 0.00592 -0.0400 0.5985 0.7372
1.750 0.4106 0.01374 0.00589 -0.0402 0.5924 0.7390
2.000 0.4382 0.01376 0.00585 -0.0405 0.5869 0.7408
2.250 0.4650 0.01377 0.00589 -0.0406 0.5803 0.7421
2.500 0.4919 0.01381 0.00592 -0.0406 0.5746 0.7430
2.750 0.5185 0.01386 0.00598 -0.0406 0.5687 0.7441
3.000 0.5450 0.01391 0.00606 -0.0405 0.5623 0.7452
3.250 0.5719 0.01398 0.00611 -0.0406 0.5567 0.7463
3.500 0.5980 0.01403 0.00623 -0.0405 0.5497 0.7476
3.750 0.6243 0.01409 0.00630 -0.0404 0.5431 0.7491
4.000 0.6505 0.01417 0.00641 -0.0404 0.5360 0.7507
4.250 0.6764 0.01424 0.00651 -0.0403 0.5284 0.7525
4.500 0.7026 0.01433 0.00661 -0.0402 0.5215 0.7543
4.750 0.7284 0.01441 0.00674 -0.0401 0.5135 0.7559
5.000 0.7544 0.01450 0.00685 -0.0401 0.5062 0.7575
5.250 0.7791 0.01459 0.00700 -0.0397 0.4975 0.7587
5.500 0.8036 0.01470 0.00717 -0.0393 0.4890 0.7599
5.750 0.8276 0.01481 0.00733 -0.0388 0.4795 0.7613
6.000 0.8513 0.01493 0.00753 -0.0383 0.4696 0.7628
6.250 0.8747 0.01507 0.00772 -0.0377 0.4597 0.7644
6.500 0.8976 0.01521 0.00793 -0.0370 0.4486 0.7663
6.750 0.9201 0.01537 0.00815 -0.0363 0.4366 0.7684
7.000 0.9418 0.01555 0.00839 -0.0355 0.4233 0.7707
7.250 0.9627 0.01576 0.00862 -0.0345 0.4081 0.7728
7.500 0.9817 0.01599 0.00889 -0.0332 0.3907 0.7746
7.750 0.9986 0.01627 0.00920 -0.0315 0.3713 0.7762
8.000 1.0135 0.01662 0.00954 -0.0295 0.3492 0.7782
8.250 1.0255 0.01704 0.00993 -0.0271 0.3248 0.7804
8.500 1.0337 0.01752 0.01036 -0.0240 0.2999 0.7828
8.750 1.0400 0.01816 0.01092 -0.0208 0.2752 0.7855
9.000 1.0466 0.01891 0.01159 -0.0179 0.2504 0.7883
9.250 1.0516 0.01974 0.01237 -0.0148 0.2275 0.7909
9.500 1.0560 0.02063 0.01323 -0.0119 0.2060 0.7936
9.750 1.0595 0.02164 0.01419 -0.0090 0.1861 0.7969
10.000 1.0642 0.02269 0.01522 -0.0066 0.1673 0.8004
10.250 1.0681 0.02386 0.01637 -0.0043 0.1494 0.8040
10.500 1.0717 0.02510 0.01760 -0.0022 0.1339 0.8071
10.750 1.0752 0.02640 0.01891 -0.0002 0.1201 0.8104
11.000 1.0792 0.02777 0.02030 0.0016 0.1080 0.8142
11.250 1.0833 0.02925 0.02181 0.0031 0.0968 0.8184
11.500 1.0868 0.03083 0.02342 0.0045 0.0865 0.8225
11.750 1.0894 0.03255 0.02517 0.0057 0.0777 0.8267
12.000 1.0935 0.03425 0.02693 0.0068 0.0694 0.8317
12.250 1.0972 0.03607 0.02881 0.0076 0.0623 0.8372
12.500 1.0985 0.03808 0.03088 0.0085 0.0563 0.8431
12.750 1.1020 0.04002 0.03291 0.0092 0.0506 0.8501
13.000 1.1035 0.04215 0.03513 0.0098 0.0459 0.8582
13.500 1.1062 0.04664 0.03984 0.0108 0.0381 0.8810
13.750 1.1074 0.04899 0.04233 0.0111 0.0348 0.9014
14.750 1.1122 0.05994 0.05367 0.0093 0.0249 1.0000
15.000 1.1111 0.06320 0.05698 0.0085 0.0231 1.0000
15.250 1.1115 0.06637 0.06025 0.0077 0.0215 1.0000
15.500 1.1119 0.06961 0.06358 0.0068 0.0195 1.0000
15.750 1.1085 0.07342 0.06748 0.0056 0.0186 1.0000
16.000 1.1083 0.07690 0.07109 0.0045 0.0170 1.0000
16.250 1.1059 0.08076 0.07506 0.0031 0.0161 1.0000
16.500 1.1012 0.08507 0.07943 0.0015 0.0151 1.0000
16.750 1.0985 0.08916 0.08367 -0.0001 0.0141 1.0000
17.000 1.0946 0.09351 0.08814 -0.0019 0.0133 1.0000
17.250 1.0893 0.09820 0.09293 -0.0040 0.0126 1.0000
17.500 1.0835 0.10308 0.09792 -0.0062 0.0119 1.0000
17.750 1.0792 0.10781 0.10279 -0.0085 0.0110 1.0000
18.000 1.0730 0.11292 0.10802 -0.0110 0.0105 1.0000
18.250 1.0673 0.11805 0.11326 -0.0136 0.0102 1.0000
18.500 1.0591 0.12375 0.11905 -0.0167 0.0097 1.0000
18.750 1.0530 0.12911 0.12454 -0.0196 0.0095 1.0000
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