EPPLER 542 AIRFOIL (e542-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 542 AIRFOIL (e542-il) Reynolds number: 1,000,000 Max Cl/Cd: 93.97 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e542-il-1000000-n5.txt Download as CSV file: xf-e542-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 542 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
------ -------- --------- --------- -------- -------- --------
-15.750 -0.7764 0.07239 0.06998 -0.0657 1.0000 0.0020
-15.500 -0.8072 0.06332 0.06071 -0.0706 1.0000 0.0020
-15.250 -0.8320 0.05675 0.05396 -0.0728 1.0000 0.0020
-15.000 -0.8483 0.05214 0.04919 -0.0734 1.0000 0.0020
-14.750 -0.8727 0.04718 0.04402 -0.0729 1.0000 0.0020
-14.500 -0.8786 0.04450 0.04121 -0.0718 1.0000 0.0020
-14.250 -0.8848 0.04197 0.03855 -0.0704 1.0000 0.0020
-14.000 -0.8958 0.03913 0.03553 -0.0683 1.0000 0.0020
-13.750 -0.8933 0.03759 0.03390 -0.0668 1.0000 0.0020
-13.500 -0.8982 0.03545 0.03162 -0.0644 1.0000 0.0020
-13.000 -0.8954 0.02979 0.02548 -0.0631 0.9968 0.0022
-12.750 -0.8839 0.02873 0.02436 -0.0619 0.9874 0.0023
-12.500 -0.8672 0.02715 0.02264 -0.0622 0.9621 0.0024
-12.250 -0.8255 0.02563 0.02099 -0.0675 0.9494 0.0024
-12.000 -0.7755 0.02413 0.01934 -0.0744 0.9392 0.0025
-11.750 -0.7222 0.02266 0.01769 -0.0820 0.9262 0.0026
-11.500 -0.6733 0.02180 0.01666 -0.0881 0.8981 0.0028
-11.250 -0.6535 0.02104 0.01568 -0.0879 0.8703 0.0029
-11.000 -0.6413 0.02016 0.01459 -0.0860 0.8480 0.0028
-10.750 -0.6254 0.01966 0.01397 -0.0846 0.8312 0.0029
-10.500 -0.6103 0.01907 0.01327 -0.0831 0.8177 0.0029
-10.250 -0.5928 0.01866 0.01276 -0.0819 0.8060 0.0031
-9.750 -0.5594 0.01764 0.01155 -0.0792 0.7842 0.0031
-9.500 -0.5425 0.01714 0.01096 -0.0778 0.7742 0.0033
-9.250 -0.5265 0.01656 0.01029 -0.0763 0.7648 0.0032
-9.000 -0.5063 0.01631 0.00998 -0.0754 0.7568 0.0033
-8.750 -0.4887 0.01585 0.00944 -0.0741 0.7487 0.0034
-8.500 -0.4714 0.01537 0.00889 -0.0727 0.7416 0.0034
-8.250 -0.4513 0.01508 0.00855 -0.0717 0.7343 0.0035
-8.000 -0.4340 0.01464 0.00804 -0.0703 0.7273 0.0036
-7.750 -0.4153 0.01426 0.00761 -0.0691 0.7204 0.0036
-7.500 -0.3972 0.01390 0.00719 -0.0677 0.7130 0.0038
-7.250 -0.3784 0.01354 0.00680 -0.0665 0.7071 0.0040
-7.000 -0.3585 0.01328 0.00651 -0.0654 0.7009 0.0042
-6.750 -0.3395 0.01300 0.00617 -0.0642 0.6953 0.0045
-6.500 -0.3199 0.01272 0.00586 -0.0630 0.6900 0.0049
-6.250 -0.3005 0.01245 0.00556 -0.0618 0.6841 0.0053
-6.000 -0.2822 0.01217 0.00524 -0.0604 0.6789 0.0058
-5.750 -0.2634 0.01188 0.00493 -0.0590 0.6735 0.0074
-5.500 -0.2446 0.01162 0.00466 -0.0576 0.6683 0.0092
-5.250 -0.2266 0.01138 0.00440 -0.0561 0.6636 0.0124
-5.000 -0.2093 0.01108 0.00413 -0.0545 0.6595 0.0200
-4.750 -0.1928 0.01080 0.00388 -0.0526 0.6549 0.0295
-4.500 -0.1781 0.01056 0.00366 -0.0504 0.6501 0.0403
-4.250 -0.1663 0.01035 0.00349 -0.0476 0.6457 0.0550
-4.000 -0.1531 0.01005 0.00331 -0.0450 0.6415 0.0844
-3.750 -0.1437 0.00955 0.00307 -0.0419 0.6373 0.1493
-3.500 -0.1321 0.00908 0.00283 -0.0392 0.6334 0.2167
-3.250 -0.1199 0.00857 0.00259 -0.0367 0.6299 0.2940
-3.000 -0.1123 0.00772 0.00222 -0.0334 0.6263 0.4224
-2.750 -0.1080 0.00644 0.00166 -0.0297 0.6225 0.6096
-2.500 -0.0865 0.00619 0.00174 -0.0286 0.6186 0.7091
-2.000 -0.0300 0.00639 0.00189 -0.0289 0.6121 0.7375
-1.750 -0.0014 0.00652 0.00198 -0.0292 0.6088 0.7468
-1.500 0.0272 0.00675 0.00222 -0.0293 0.6052 0.7545
-1.250 0.0556 0.00683 0.00224 -0.0295 0.6017 0.7575
-0.750 0.1127 0.00684 0.00216 -0.0303 0.5956 0.7589
-0.500 0.1414 0.00684 0.00213 -0.0307 0.5923 0.7596
-0.250 0.1699 0.00685 0.00210 -0.0311 0.5889 0.7601
0.000 0.1982 0.00687 0.00207 -0.0314 0.5855 0.7605
0.250 0.2263 0.00689 0.00205 -0.0317 0.5822 0.7611
0.500 0.2550 0.00688 0.00204 -0.0321 0.5792 0.7617
0.750 0.2835 0.00689 0.00203 -0.0325 0.5755 0.7622
1.000 0.3117 0.00691 0.00204 -0.0328 0.5713 0.7628
1.250 0.3392 0.00696 0.00205 -0.0330 0.5667 0.7634
1.500 0.3677 0.00697 0.00207 -0.0334 0.5623 0.7640
1.750 0.3958 0.00700 0.00209 -0.0337 0.5576 0.7646
2.000 0.4235 0.00705 0.00212 -0.0339 0.5529 0.7651
2.250 0.4513 0.00709 0.00215 -0.0342 0.5484 0.7657
2.500 0.4795 0.00712 0.00218 -0.0345 0.5434 0.7662
2.750 0.5069 0.00717 0.00222 -0.0347 0.5376 0.7668
3.000 0.5343 0.00722 0.00226 -0.0348 0.5322 0.7673
3.250 0.5620 0.00726 0.00231 -0.0351 0.5260 0.7679
3.500 0.5886 0.00734 0.00237 -0.0351 0.5191 0.7685
3.750 0.6161 0.00739 0.00242 -0.0353 0.5118 0.7691
4.000 0.6422 0.00748 0.00249 -0.0353 0.5031 0.7697
4.250 0.6689 0.00755 0.00256 -0.0353 0.4930 0.7703
4.500 0.6948 0.00766 0.00264 -0.0352 0.4823 0.7709
4.750 0.7197 0.00779 0.00274 -0.0350 0.4687 0.7716
5.000 0.7441 0.00794 0.00285 -0.0346 0.4527 0.7723
5.250 0.7668 0.00816 0.00299 -0.0339 0.4306 0.7731
5.500 0.7875 0.00844 0.00318 -0.0329 0.4042 0.7738
5.750 0.8066 0.00879 0.00340 -0.0315 0.3749 0.7744
6.000 0.8247 0.00916 0.00365 -0.0300 0.3461 0.7750
6.250 0.8425 0.00952 0.00390 -0.0285 0.3188 0.7755
6.500 0.8593 0.00990 0.00417 -0.0267 0.2928 0.7760
6.750 0.8726 0.01027 0.00444 -0.0243 0.2678 0.7767
7.000 0.8871 0.01058 0.00468 -0.0221 0.2479 0.7776
7.250 0.9008 0.01094 0.00498 -0.0198 0.2284 0.7784
7.750 0.9259 0.01182 0.00571 -0.0149 0.1887 0.7800
8.000 0.9351 0.01238 0.00617 -0.0120 0.1651 0.7809
8.250 0.9446 0.01294 0.00665 -0.0093 0.1446 0.7817
8.500 0.9548 0.01349 0.00714 -0.0067 0.1275 0.7825
8.750 0.9669 0.01400 0.00762 -0.0046 0.1161 0.7834
9.000 0.9763 0.01463 0.00819 -0.0022 0.1014 0.7844
9.250 0.9857 0.01530 0.00881 0.0002 0.0886 0.7854
9.500 0.9891 0.01625 0.00966 0.0032 0.0694 0.7865
9.750 1.0013 0.01688 0.01029 0.0049 0.0632 0.7874
10.000 1.0055 0.01791 0.01123 0.0075 0.0478 0.7883
10.250 1.0124 0.01888 0.01215 0.0097 0.0379 0.7891
10.500 1.0269 0.01950 0.01282 0.0108 0.0374 0.7899
10.750 1.0341 0.02053 0.01381 0.0127 0.0290 0.7907
11.000 1.0425 0.02155 0.01480 0.0143 0.0232 0.7913
11.250 1.0539 0.02242 0.01570 0.0155 0.0213 0.7919
11.500 1.0646 0.02337 0.01667 0.0168 0.0188 0.7926
11.750 1.0723 0.02450 0.01781 0.0182 0.0150 0.7936
12.000 1.0831 0.02548 0.01883 0.0193 0.0136 0.7946
12.250 1.0920 0.02662 0.01999 0.0204 0.0116 0.7955
12.500 1.1015 0.02774 0.02116 0.0215 0.0102 0.7965
12.750 1.1119 0.02884 0.02230 0.0223 0.0097 0.7974
13.000 1.1212 0.03004 0.02355 0.0232 0.0085 0.7982
13.250 1.1289 0.03139 0.02493 0.0242 0.0070 0.7991
13.500 1.1378 0.03269 0.02628 0.0249 0.0061 0.8001
13.750 1.1451 0.03415 0.02777 0.0257 0.0048 0.8012
14.000 1.1527 0.03563 0.02929 0.0264 0.0042 0.8022
14.250 1.1575 0.03738 0.03107 0.0271 0.0028 0.8033
14.500 1.1657 0.03890 0.03266 0.0276 0.0027 0.8042
14.750 1.1731 0.04053 0.03434 0.0280 0.0025 0.8050
15.000 1.1782 0.04239 0.03625 0.0284 0.0019 0.8059
15.250 1.1848 0.04417 0.03810 0.0287 0.0018 0.8066
15.500 1.1872 0.04640 0.04039 0.0290 0.0011 0.8074
15.750 1.1932 0.04835 0.04240 0.0291 0.0010 0.8080
16.000 1.1975 0.05049 0.04461 0.0291 0.0009 0.8088
16.250 1.2026 0.05259 0.04679 0.0291 0.0009 0.8098
16.500 1.2067 0.05485 0.04912 0.0290 0.0008 0.8108
16.750 1.2089 0.05739 0.05174 0.0287 0.0007 0.8118
17.000 1.2117 0.05993 0.05437 0.0284 0.0006 0.8128
17.250 1.2135 0.06262 0.05714 0.0280 0.0006 0.8137
17.500 1.2154 0.06538 0.05998 0.0274 0.0006 0.8147
17.750 1.2101 0.06912 0.06383 0.0266 0.0004 0.8156
18.000 1.2138 0.07180 0.06659 0.0258 0.0004 0.8166
18.250 1.2144 0.07494 0.06982 0.0249 0.0004 0.8175
18.500 1.2147 0.07819 0.07316 0.0238 0.0005 0.8184
18.750 1.2064 0.08276 0.07786 0.0223 0.0004 0.8193
19.000 1.2027 0.08678 0.08199 0.0207 0.0004 0.8201
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Polar data table (+)
Polar graphs
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