E475 (15.01%) (e475-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: E475 (15.01%) (e475-il) Reynolds number: 50,000 Max Cl/Cd: 20.16 at α=3.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e475-il-50000.txt Download as CSV file: xf-e475-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: E475 (15.01%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.4425 0.12034 0.11134 0.0046 1.0000 0.4248
-10.250 -0.4090 0.11509 0.10604 0.0040 1.0000 0.4321
-10.000 -0.4192 0.11362 0.10459 0.0048 1.0000 0.4440
-9.750 -0.4049 0.11096 0.10190 0.0053 1.0000 0.4580
-9.500 -0.3856 0.10725 0.09817 0.0052 1.0000 0.4675
-9.250 -0.3934 0.10559 0.09655 0.0063 1.0000 0.4792
-9.000 -0.3801 0.10304 0.09398 0.0068 1.0000 0.4925
-8.750 -0.3608 0.09971 0.09062 0.0068 1.0000 0.5038
-8.500 -0.3570 0.09743 0.08836 0.0077 1.0000 0.5168
-8.250 -0.3635 0.09602 0.08699 0.0094 1.0000 0.5308
-8.000 -0.3386 0.09272 0.08366 0.0091 1.0000 0.5426
-7.750 -0.6298 0.06755 0.05885 -0.0034 1.0000 0.3564
-7.500 -0.6688 0.06201 0.05330 -0.0008 1.0000 0.3547
-7.250 -0.7093 0.05680 0.04800 0.0029 1.0000 0.3548
-7.000 -0.6869 0.05556 0.04679 0.0044 1.0000 0.3608
-6.750 -0.6992 0.05234 0.04349 0.0074 1.0000 0.3642
-6.500 -0.7157 0.04881 0.03980 0.0109 1.0000 0.3672
-6.250 -0.7314 0.04538 0.03611 0.0145 1.0000 0.3709
-6.000 -0.7256 0.04329 0.03393 0.0169 1.0000 0.3762
-5.750 -0.7129 0.04183 0.03243 0.0189 1.0000 0.3825
-5.500 -0.7132 0.03949 0.02981 0.0217 1.0000 0.3884
-5.250 -0.7002 0.03790 0.02815 0.0236 1.0000 0.3940
-5.000 -0.6858 0.03661 0.02681 0.0254 1.0000 0.4010
-4.750 -0.6794 0.03484 0.02476 0.0278 1.0000 0.4084
-4.500 -0.6590 0.03391 0.02393 0.0292 1.0000 0.4155
-4.250 -0.6470 0.03254 0.02234 0.0310 1.0000 0.4233
-4.000 -0.6289 0.03153 0.02136 0.0325 1.0000 0.4310
-3.750 -0.6136 0.03050 0.02021 0.0342 1.0000 0.4404
-3.500 -0.5951 0.02962 0.01936 0.0356 1.0000 0.4489
-3.250 -0.5788 0.02870 0.01830 0.0370 1.0000 0.4589
-3.000 -0.5591 0.02799 0.01770 0.0383 1.0000 0.4686
-2.750 -0.5414 0.02725 0.01691 0.0396 1.0000 0.4799
-2.500 -0.5225 0.02664 0.01632 0.0408 1.0000 0.4919
-2.250 -0.5031 0.02609 0.01586 0.0420 1.0000 0.5040
-2.000 -0.4846 0.02557 0.01541 0.0431 1.0000 0.5182
-1.750 -0.4665 0.02513 0.01505 0.0443 1.0000 0.5341
-1.500 -0.4484 0.02475 0.01479 0.0455 1.0000 0.5518
-1.250 -0.4305 0.02444 0.01464 0.0465 1.0000 0.5719
-1.000 -0.4139 0.02421 0.01458 0.0475 1.0000 0.5963
-0.750 -0.3991 0.02407 0.01471 0.0488 1.0000 0.6244
-0.500 -0.3579 0.02430 0.01540 0.0453 0.9874 0.6752
-0.250 -0.2364 0.02551 0.01758 0.0309 0.9513 0.7992
0.000 0.0000 0.02775 0.01995 0.0000 0.9028 0.9028
0.250 0.2364 0.02550 0.01758 -0.0309 0.7991 0.9513
0.500 0.3579 0.02430 0.01540 -0.0453 0.6751 0.9874
0.750 0.3991 0.02407 0.01471 -0.0488 0.6244 1.0000
1.000 0.4139 0.02421 0.01458 -0.0475 0.5964 1.0000
1.250 0.4304 0.02444 0.01464 -0.0465 0.5719 1.0000
1.500 0.4483 0.02474 0.01478 -0.0454 0.5518 1.0000
1.750 0.4664 0.02513 0.01505 -0.0443 0.5342 1.0000
2.000 0.4846 0.02557 0.01541 -0.0431 0.5183 1.0000
2.250 0.5030 0.02608 0.01586 -0.0420 0.5042 1.0000
2.500 0.5224 0.02664 0.01632 -0.0408 0.4919 1.0000
2.750 0.5413 0.02725 0.01691 -0.0396 0.4800 1.0000
3.000 0.5590 0.02799 0.01769 -0.0383 0.4686 1.0000
3.250 0.5787 0.02870 0.01830 -0.0370 0.4589 1.0000
3.500 0.5950 0.02961 0.01936 -0.0355 0.4489 1.0000
3.750 0.6135 0.03050 0.02020 -0.0341 0.4404 1.0000
4.000 0.6288 0.03154 0.02137 -0.0325 0.4310 1.0000
4.250 0.6469 0.03253 0.02233 -0.0310 0.4234 1.0000
4.500 0.6589 0.03390 0.02392 -0.0292 0.4155 1.0000
4.750 0.6792 0.03484 0.02476 -0.0278 0.4085 1.0000
5.000 0.6857 0.03661 0.02681 -0.0254 0.4011 1.0000
5.250 0.7001 0.03790 0.02816 -0.0236 0.3941 1.0000
5.500 0.7133 0.03948 0.02980 -0.0217 0.3885 1.0000
5.750 0.7129 0.04183 0.03243 -0.0189 0.3826 1.0000
6.000 0.7255 0.04328 0.03392 -0.0169 0.3762 1.0000
6.250 0.7313 0.04536 0.03609 -0.0144 0.3709 1.0000
6.500 0.7158 0.04880 0.03979 -0.0109 0.3672 1.0000
6.750 0.6991 0.05234 0.04349 -0.0074 0.3643 1.0000
7.000 0.6814 0.05594 0.04719 -0.0042 0.3615 1.0000
7.250 0.6549 0.06016 0.05145 -0.0009 0.3600 1.0000
7.500 0.6377 0.06394 0.05524 0.0016 0.3580 1.0000
7.750 0.6297 0.06756 0.05885 0.0034 0.3564 1.0000
8.000 0.3398 0.09275 0.08369 -0.0092 0.5430 1.0000
8.250 0.3634 0.09592 0.08689 -0.0094 0.5309 1.0000
8.500 0.3581 0.09741 0.08834 -0.0078 0.5167 1.0000
8.750 0.3616 0.09967 0.09058 -0.0069 0.5039 1.0000
9.000 0.3812 0.10303 0.09397 -0.0069 0.4926 1.0000
9.250 0.3938 0.10555 0.09650 -0.0064 0.4793 1.0000
9.500 0.3866 0.10724 0.09816 -0.0053 0.4673 1.0000
9.750 0.4055 0.11092 0.10186 -0.0054 0.4580 1.0000
10.000 0.4221 0.11378 0.10475 -0.0050 0.4438 1.0000
10.250 0.4101 0.11508 0.10602 -0.0041 0.4320 1.0000
10.500 0.4434 0.12031 0.11131 -0.0047 0.4248 1.0000
|
Polar data table (+)
Polar graphs
<< Back to E475 (15.01%) (e475-il)