EPPLER 407 AIRFOIL (e407-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: EPPLER 407 AIRFOIL (e407-il) Reynolds number: 100,000 Max Cl/Cd: 48.23 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e407-il-100000-n5.txt Download as CSV file: xf-e407-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 407 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.5092 0.09804 0.09335 -0.0519 0.9974 0.0177
-10.500 -0.5250 0.08830 0.08358 -0.0589 0.9950 0.0173
-10.250 -0.5460 0.07957 0.07473 -0.0657 0.9919 0.0170
-10.000 -0.5646 0.07311 0.06813 -0.0705 0.9880 0.0167
-9.750 -0.5848 0.06732 0.06214 -0.0745 0.9842 0.0167
-9.500 -0.6032 0.06319 0.05783 -0.0758 0.9792 0.0164
-9.250 -0.6208 0.05991 0.05437 -0.0759 0.9738 0.0163
-9.000 -0.6313 0.05610 0.05027 -0.0773 0.9689 0.0163
-8.750 -0.6380 0.05257 0.04641 -0.0770 0.9632 0.0165
-8.500 -0.6329 0.04890 0.04233 -0.0778 0.9595 0.0166
-8.250 -0.6209 0.04526 0.03821 -0.0788 0.9566 0.0169
-8.000 -0.6133 0.04256 0.03515 -0.0775 0.9522 0.0172
-7.750 -0.5968 0.03997 0.03212 -0.0773 0.9493 0.0177
-7.500 -0.5748 0.03770 0.02945 -0.0774 0.9470 0.0183
-7.250 -0.5498 0.03584 0.02731 -0.0777 0.9451 0.0190
-7.000 -0.5299 0.03429 0.02574 -0.0778 0.9426 0.0208
-6.750 -0.5126 0.03327 0.02462 -0.0769 0.9391 0.0232
-6.500 -0.4896 0.03212 0.02328 -0.0765 0.9362 0.0257
-6.250 -0.4656 0.03060 0.02171 -0.0768 0.9339 0.0283
-6.000 -0.4376 0.02959 0.02063 -0.0779 0.9320 0.0335
-5.750 -0.4113 0.02852 0.01949 -0.0789 0.9298 0.0410
-5.500 -0.3910 0.02758 0.01855 -0.0785 0.9259 0.0525
-5.250 -0.3638 0.02669 0.01769 -0.0796 0.9231 0.0733
-5.000 -0.3327 0.02556 0.01686 -0.0818 0.9210 0.1190
-4.750 -0.2973 0.02424 0.01606 -0.0854 0.9195 0.2221
-4.500 -0.2617 0.02299 0.01595 -0.0888 0.9183 0.4294
-4.250 -0.2407 0.02343 0.01659 -0.0870 0.9145 0.5165
-4.000 -0.2172 0.02390 0.01695 -0.0860 0.9103 0.5543
-3.750 -0.1887 0.02439 0.01728 -0.0859 0.9072 0.5794
-3.500 -0.1588 0.02491 0.01765 -0.0858 0.9048 0.5979
-3.250 -0.1367 0.02533 0.01794 -0.0845 0.9007 0.6110
-3.000 -0.1146 0.02568 0.01818 -0.0833 0.8961 0.6227
-2.750 -0.0853 0.02596 0.01831 -0.0835 0.8930 0.6343
-2.500 -0.0552 0.02627 0.01851 -0.0837 0.8906 0.6444
-2.250 -0.0376 0.02655 0.01872 -0.0816 0.8851 0.6518
-2.000 -0.0082 0.02664 0.01867 -0.0825 0.8812 0.6616
-1.750 0.0200 0.02676 0.01873 -0.0823 0.8781 0.6657
-1.500 0.0548 0.02673 0.01859 -0.0839 0.8760 0.6703
-1.250 0.0776 0.02673 0.01847 -0.0841 0.8694 0.6760
-1.000 0.1062 0.02673 0.01843 -0.0843 0.8656 0.6787
-0.750 0.1399 0.02668 0.01832 -0.0857 0.8630 0.6820
-0.500 0.1633 0.02674 0.01832 -0.0855 0.8570 0.6861
-0.250 0.1963 0.02668 0.01817 -0.0873 0.8527 0.6907
0.000 0.2289 0.02660 0.01808 -0.0882 0.8497 0.6932
0.250 0.2518 0.02668 0.01815 -0.0877 0.8434 0.6962
0.500 0.2822 0.02663 0.01808 -0.0886 0.8384 0.6997
0.750 0.3209 0.02645 0.01786 -0.0911 0.8356 0.7039
1.000 0.3424 0.02654 0.01797 -0.0904 0.8278 0.7067
1.250 0.3740 0.02640 0.01786 -0.0912 0.8234 0.7093
1.500 0.4113 0.02615 0.01762 -0.0930 0.8206 0.7125
1.750 0.4322 0.02629 0.01779 -0.0923 0.8112 0.7163
2.000 0.4706 0.02598 0.01750 -0.0945 0.8078 0.7197
2.250 0.4910 0.02607 0.01765 -0.0933 0.7987 0.7222
2.500 0.5256 0.02573 0.01738 -0.0944 0.7944 0.7252
2.750 0.5501 0.02573 0.01746 -0.0941 0.7855 0.7286
3.000 0.5874 0.02531 0.01709 -0.0958 0.7806 0.7323
3.250 0.6121 0.02523 0.01710 -0.0954 0.7711 0.7351
3.500 0.6466 0.02469 0.01668 -0.0961 0.7660 0.7379
3.750 0.6702 0.02461 0.01669 -0.0954 0.7554 0.7413
4.000 0.7096 0.02391 0.01609 -0.0971 0.7504 0.7449
4.250 0.7351 0.02380 0.01610 -0.0968 0.7381 0.7484
4.750 0.7871 0.02328 0.01584 -0.0956 0.7126 0.7544
5.000 0.8173 0.02293 0.01562 -0.0957 0.6981 0.7582
5.500 0.8840 0.02202 0.01492 -0.0968 0.6630 0.7650
5.750 0.9174 0.02159 0.01455 -0.0972 0.6382 0.7682
6.000 0.9548 0.02115 0.01415 -0.0983 0.6062 0.7720
6.250 0.9915 0.02097 0.01388 -0.0994 0.5653 0.7762
6.500 1.0186 0.02112 0.01391 -0.0990 0.5212 0.7794
6.750 1.0392 0.02158 0.01421 -0.0977 0.4751 0.7829
7.000 1.0563 0.02225 0.01471 -0.0960 0.4299 0.7870
7.250 1.0713 0.02305 0.01538 -0.0942 0.3864 0.7914
7.500 1.0824 0.02391 0.01609 -0.0917 0.3460 0.7952
7.750 1.0937 0.02486 0.01690 -0.0895 0.3058 0.7996
8.000 1.1060 0.02590 0.01780 -0.0876 0.2675 0.8044
8.250 1.1157 0.02698 0.01875 -0.0853 0.2319 0.8084
8.500 1.1263 0.02810 0.01977 -0.0832 0.1984 0.8129
8.750 1.1376 0.02932 0.02087 -0.0814 0.1673 0.8182
9.000 1.1478 0.03052 0.02201 -0.0794 0.1413 0.8230
9.250 1.1575 0.03183 0.02329 -0.0775 0.1191 0.8283
9.500 1.1689 0.03317 0.02462 -0.0759 0.0995 0.8340
9.750 1.1773 0.03455 0.02601 -0.0738 0.0839 0.8393
10.000 1.1864 0.03605 0.02753 -0.0720 0.0716 0.8456
10.250 1.1940 0.03757 0.02913 -0.0699 0.0620 0.8520
10.500 1.1992 0.03936 0.03092 -0.0679 0.0551 0.8593
10.750 1.2067 0.04091 0.03268 -0.0659 0.0491 0.8671
11.000 1.2104 0.04288 0.03469 -0.0639 0.0444 0.8760
11.250 1.2164 0.04452 0.03655 -0.0618 0.0401 0.8866
11.500 1.2203 0.04631 0.03850 -0.0597 0.0370 0.9007
11.750 1.2202 0.04825 0.04060 -0.0573 0.0347 0.9250
12.000 1.2218 0.05036 0.04287 -0.0555 0.0324 1.0000
12.250 1.2312 0.05267 0.04539 -0.0550 0.0294 1.0000
12.500 1.2378 0.05520 0.04805 -0.0545 0.0272 1.0000
12.750 1.2421 0.05803 0.05098 -0.0539 0.0256 1.0000
13.000 1.2461 0.06117 0.05423 -0.0533 0.0241 1.0000
13.250 1.2511 0.06414 0.05750 -0.0529 0.0224 1.0000
13.500 1.2531 0.06735 0.06095 -0.0527 0.0209 1.0000
13.750 1.2532 0.07081 0.06459 -0.0526 0.0198 1.0000
14.000 1.2520 0.07454 0.06850 -0.0527 0.0190 1.0000
14.250 1.2492 0.07854 0.07265 -0.0531 0.0184 1.0000
14.500 1.2442 0.08296 0.07722 -0.0537 0.0177 1.0000
14.750 1.2361 0.08807 0.08255 -0.0547 0.0172 1.0000
15.000 1.2260 0.09359 0.08839 -0.0564 0.0168 1.0000
15.250 1.2139 0.09965 0.09475 -0.0587 0.0164 1.0000
15.500 1.2001 0.10629 0.10167 -0.0618 0.0161 1.0000
15.750 1.1847 0.11355 0.10920 -0.0657 0.0159 1.0000
16.000 1.1682 0.12152 0.11741 -0.0704 0.0159 1.0000
16.250 1.1502 0.13032 0.12644 -0.0761 0.0160 1.0000
16.500 1.1310 0.14003 0.13635 -0.0826 0.0162 1.0000
16.750 1.1106 0.15076 0.14725 -0.0901 0.0165 1.0000
17.000 1.0908 0.16211 0.15871 -0.0979 0.0169 1.0000
17.250 1.0715 0.17422 0.17088 -0.1059 0.0172 1.0000
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