EPPLER 540 AIRFOIL (e540-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 540 AIRFOIL (e540-il) Reynolds number: 500,000 Max Cl/Cd: 85.34 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e540-il-500000.txt Download as CSV file: xf-e540-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 540 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
------ -------- --------- --------- -------- -------- --------
-12.000 -0.3184 0.08339 0.08138 -0.0783 0.9819 0.0191
-11.750 -0.3549 0.06990 0.06781 -0.0864 0.9766 0.0182
-11.500 -0.5205 0.06847 0.06602 -0.0820 0.9963 0.0162
-11.250 -0.5293 0.06316 0.06058 -0.0857 0.9896 0.0164
-11.000 -0.5392 0.05853 0.05580 -0.0877 0.9756 0.0165
-10.750 -0.5425 0.05470 0.05182 -0.0897 0.9634 0.0167
-10.500 -0.5393 0.05081 0.04774 -0.0926 0.9546 0.0171
-10.250 -0.5285 0.04677 0.04344 -0.0966 0.9463 0.0175
-10.000 -0.5133 0.04290 0.03928 -0.1003 0.9346 0.0182
-9.750 -0.5019 0.03982 0.03587 -0.1014 0.9178 0.0191
-9.500 -0.4805 0.01595 0.01080 -0.0946 0.8841 0.0106
-9.250 -0.4848 0.02697 0.02151 -0.0964 0.8930 0.0097
-9.000 -0.4490 0.02330 0.01742 -0.0980 0.8880 0.0088
-8.750 -0.4144 0.02145 0.01531 -0.0988 0.8817 0.0084
-8.500 -0.3836 0.02015 0.01382 -0.0991 0.8747 0.0084
-8.250 -0.3599 0.01922 0.01275 -0.0984 0.8671 0.0085
-8.000 -0.3400 0.01852 0.01193 -0.0974 0.8592 0.0084
-7.750 -0.3234 0.01784 0.01116 -0.0958 0.8513 0.0088
-7.500 -0.3072 0.01722 0.01044 -0.0943 0.8443 0.0094
-7.250 -0.2904 0.01676 0.00991 -0.0927 0.8375 0.0101
-7.000 -0.2804 0.01593 0.00898 -0.0903 0.8311 0.0107
-6.750 -0.2680 0.01529 0.00830 -0.0881 0.8252 0.0121
-6.500 -0.2528 0.01483 0.00778 -0.0864 0.8196 0.0139
-6.250 -0.2397 0.01425 0.00714 -0.0843 0.8147 0.0198
-6.000 -0.2333 0.01349 0.00651 -0.0810 0.8088 0.0437
-5.750 -0.2271 0.01280 0.00600 -0.0779 0.8036 0.0842
-5.500 -0.2247 0.01216 0.00556 -0.0740 0.7990 0.1339
-5.250 -0.2300 0.01147 0.00517 -0.0687 0.7937 0.2010
-5.000 -0.2342 0.01049 0.00465 -0.0637 0.7891 0.3104
-4.750 -0.2426 0.00905 0.00391 -0.0582 0.7848 0.4792
-4.500 -0.2346 0.00851 0.00412 -0.0546 0.7806 0.6619
-4.250 -0.2072 0.00884 0.00436 -0.0544 0.7773 0.6900
-4.000 -0.1786 0.00925 0.00468 -0.0544 0.7746 0.7038
-3.750 -0.1476 0.00982 0.00522 -0.0546 0.7722 0.7125
-3.500 -0.1203 0.01013 0.00548 -0.0544 0.7691 0.7204
-3.250 -0.0901 0.01074 0.00611 -0.0542 0.7660 0.7264
-3.000 -0.0607 0.01136 0.00670 -0.0540 0.7632 0.7349
-2.750 -0.0252 0.01268 0.00805 -0.0538 0.7609 0.7413
-2.500 0.0025 0.01299 0.00827 -0.0537 0.7585 0.7486
-2.250 0.0304 0.01305 0.00832 -0.0538 0.7559 0.7496
-2.000 0.0575 0.01307 0.00830 -0.0538 0.7528 0.7506
-1.750 0.0849 0.01306 0.00826 -0.0539 0.7501 0.7519
-1.500 0.1125 0.01302 0.00817 -0.0542 0.7476 0.7534
-1.250 0.1403 0.01295 0.00804 -0.0546 0.7452 0.7552
-1.000 0.1668 0.01279 0.00782 -0.0550 0.7427 0.7577
-0.750 0.1912 0.01244 0.00741 -0.0554 0.7397 0.7612
-0.500 0.2179 0.01234 0.00730 -0.0555 0.7368 0.7620
-0.250 0.2455 0.01226 0.00719 -0.0557 0.7341 0.7628
0.000 0.2739 0.01219 0.00710 -0.0562 0.7315 0.7635
0.250 0.3024 0.01220 0.00708 -0.0566 0.7289 0.7643
0.500 0.3279 0.01214 0.00704 -0.0564 0.7255 0.7652
0.750 0.3549 0.01206 0.00696 -0.0566 0.7220 0.7660
1.000 0.3830 0.01197 0.00686 -0.0571 0.7188 0.7669
1.250 0.4122 0.01194 0.00678 -0.0577 0.7158 0.7679
1.500 0.4378 0.01187 0.00675 -0.0577 0.7120 0.7692
1.750 0.4645 0.01176 0.00664 -0.0579 0.7079 0.7704
2.000 0.4930 0.01165 0.00651 -0.0584 0.7040 0.7715
2.250 0.5219 0.01158 0.00641 -0.0591 0.7003 0.7725
2.500 0.5474 0.01146 0.00633 -0.0591 0.6956 0.7738
2.750 0.5756 0.01138 0.00623 -0.0596 0.6910 0.7751
3.000 0.6048 0.01131 0.00613 -0.0602 0.6870 0.7758
3.250 0.6288 0.01120 0.00611 -0.0597 0.6816 0.7765
3.500 0.6556 0.01112 0.00604 -0.0598 0.6764 0.7771
3.750 0.6831 0.01108 0.00601 -0.0600 0.6714 0.7778
4.000 0.7075 0.01100 0.00601 -0.0596 0.6650 0.7785
4.250 0.7349 0.01095 0.00595 -0.0597 0.6591 0.7793
4.500 0.7586 0.01089 0.00597 -0.0591 0.6518 0.7801
4.750 0.7849 0.01085 0.00594 -0.0591 0.6448 0.7810
5.000 0.8077 0.01079 0.00596 -0.0583 0.6357 0.7821
5.250 0.8316 0.01075 0.00595 -0.0577 0.6261 0.7832
5.500 0.8549 0.01071 0.00593 -0.0571 0.6149 0.7841
5.750 0.8770 0.01069 0.00594 -0.0562 0.6012 0.7852
6.000 0.8980 0.01069 0.00598 -0.0551 0.5847 0.7862
6.250 0.9167 0.01075 0.00601 -0.0535 0.5623 0.7873
6.500 0.9311 0.01091 0.00608 -0.0511 0.5315 0.7883
6.750 0.9388 0.01125 0.00623 -0.0475 0.4909 0.7894
7.000 0.9384 0.01164 0.00645 -0.0422 0.4497 0.7905
7.250 0.9385 0.01221 0.00685 -0.0373 0.4087 0.7917
7.500 0.9388 0.01294 0.00739 -0.0326 0.3669 0.7930
7.750 0.9417 0.01366 0.00796 -0.0287 0.3315 0.7943
8.000 0.9468 0.01437 0.00856 -0.0253 0.2990 0.7955
8.250 0.9511 0.01516 0.00922 -0.0219 0.2663 0.7968
8.500 0.9556 0.01603 0.00994 -0.0188 0.2349 0.7981
8.750 0.9618 0.01688 0.01067 -0.0161 0.2071 0.7994
9.000 0.9684 0.01779 0.01146 -0.0136 0.1801 0.8006
9.250 0.9761 0.01870 0.01227 -0.0114 0.1563 0.8019
9.500 0.9836 0.01968 0.01314 -0.0093 0.1345 0.8030
9.750 0.9914 0.02066 0.01403 -0.0073 0.1131 0.8041
10.000 0.9985 0.02167 0.01498 -0.0052 0.0943 0.8053
10.250 1.0062 0.02272 0.01596 -0.0033 0.0772 0.8067
10.500 1.0133 0.02385 0.01705 -0.0015 0.0623 0.8080
10.750 1.0210 0.02499 0.01814 0.0002 0.0503 0.8093
11.000 1.0299 0.02610 0.01925 0.0017 0.0415 0.8106
11.250 1.0377 0.02733 0.02047 0.0032 0.0350 0.8119
11.500 1.0475 0.02845 0.02159 0.0044 0.0298 0.8133
11.750 1.0539 0.02985 0.02304 0.0059 0.0263 0.8147
12.000 1.0664 0.03086 0.02412 0.0067 0.0237 0.8160
12.250 1.0745 0.03222 0.02548 0.0078 0.0207 0.8172
12.500 1.0802 0.03375 0.02709 0.0091 0.0181 0.8185
12.750 1.0900 0.03500 0.02842 0.0100 0.0161 0.8198
13.000 1.0958 0.03660 0.03004 0.0110 0.0135 0.8212
13.250 1.1008 0.03834 0.03190 0.0121 0.0116 0.8226
13.500 1.1080 0.03995 0.03358 0.0129 0.0101 0.8242
13.750 1.1114 0.04195 0.03565 0.0138 0.0092 0.8259
14.000 1.1044 0.04499 0.03880 0.0151 0.0083 0.8276
14.250 1.1062 0.04731 0.04124 0.0157 0.0080 0.8293
14.500 1.1148 0.04906 0.04309 0.0159 0.0072 0.8309
14.750 1.1205 0.05111 0.04522 0.0162 0.0064 0.8325
15.000 1.1225 0.05355 0.04777 0.0164 0.0061 0.8341
15.250 1.1215 0.05642 0.05074 0.0166 0.0057 0.8357
15.500 1.1203 0.05943 0.05387 0.0166 0.0057 0.8373
15.750 1.1176 0.06272 0.05728 0.0164 0.0055 0.8391
16.000 1.0996 0.06803 0.06278 0.0163 0.0052 0.8403
16.250 1.0969 0.07163 0.06652 0.0157 0.0051 0.8420
16.500 1.0962 0.07513 0.07016 0.0148 0.0050 0.8438
16.750 1.0949 0.07883 0.07400 0.0137 0.0049 0.8455
17.000 1.0907 0.08291 0.07826 0.0126 0.0050 0.8472
17.250 1.0864 0.08725 0.08276 0.0111 0.0048 0.8490
17.500 1.0813 0.09179 0.08746 0.0094 0.0047 0.8509
17.750 1.0748 0.09670 0.09254 0.0074 0.0047 0.8527
18.000 1.0680 0.10183 0.09783 0.0050 0.0046 0.8547
18.250 1.0580 0.10764 0.10381 0.0023 0.0046 0.8566
18.500 1.0504 0.11323 0.10955 -0.0007 0.0045 0.8587
18.750 1.0374 0.11990 0.11640 -0.0041 0.0045 0.8605
19.000 1.0273 0.12616 0.12284 -0.0076 0.0045 0.8627
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