E475 (15.01%) (e475-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: E475 (15.01%) (e475-il) Reynolds number: 100,000 Max Cl/Cd: 36.29 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e475-il-100000-n5.txt Download as CSV file: xf-e475-il-100000-n5.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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.500 -0.7125 0.13987 0.13370 -0.0104 1.0000 0.0844
-15.500 -0.9536 0.07890 0.07251 -0.0429 1.0000 0.1063
-15.250 -0.8251 0.09819 0.09196 -0.0307 1.0000 0.1075
-15.000 -0.7857 0.10231 0.09608 -0.0278 1.0000 0.1083
-14.750 -1.0155 0.06098 0.05438 -0.0519 1.0000 0.1134
-14.500 -1.0497 0.05409 0.04726 -0.0550 1.0000 0.1153
-14.250 -1.0760 0.04900 0.04191 -0.0562 1.0000 0.1175
-14.000 -1.0879 0.04592 0.03868 -0.0560 1.0000 0.1200
-13.750 -1.0862 0.04443 0.03719 -0.0550 1.0000 0.1227
-13.500 -1.0898 0.04259 0.03528 -0.0537 1.0000 0.1256
-13.250 -1.0973 0.04060 0.03311 -0.0517 1.0000 0.1288
-13.000 -1.1078 0.03855 0.03078 -0.0490 1.0000 0.1320
-12.750 -1.1015 0.03777 0.03005 -0.0469 1.0000 0.1347
-12.500 -1.0982 0.03695 0.02918 -0.0442 1.0000 0.1377
-12.250 -1.0988 0.03595 0.02807 -0.0410 1.0000 0.1411
-12.000 -1.1037 0.03482 0.02672 -0.0369 1.0000 0.1446
-11.750 -1.1011 0.03409 0.02594 -0.0334 1.0000 0.1474
-11.500 -1.0937 0.03360 0.02546 -0.0305 1.0000 0.1505
-11.250 -1.0878 0.03296 0.02473 -0.0273 1.0000 0.1541
-11.000 -1.0837 0.03209 0.02366 -0.0240 1.0000 0.1581
-10.750 -1.0751 0.03140 0.02287 -0.0211 1.0000 0.1614
-10.500 -1.0632 0.03099 0.02246 -0.0186 1.0000 0.1648
-10.250 -1.0528 0.03043 0.02182 -0.0159 1.0000 0.1686
-10.000 -1.0439 0.02969 0.02086 -0.0130 1.0000 0.1729
-9.750 -1.0312 0.02911 0.02022 -0.0106 1.0000 0.1764
-9.500 -1.0168 0.02871 0.01981 -0.0084 1.0000 0.1800
-9.250 -1.0032 0.02817 0.01918 -0.0061 1.0000 0.1840
-9.000 -0.9908 0.02753 0.01832 -0.0036 1.0000 0.1885
-8.750 -0.9748 0.02703 0.01780 -0.0016 1.0000 0.1920
-8.500 -0.9584 0.02660 0.01736 0.0003 1.0000 0.1957
-8.250 -0.9425 0.02611 0.01677 0.0024 1.0000 0.1999
-8.000 -0.9272 0.02555 0.01600 0.0045 1.0000 0.2046
-7.750 -0.9090 0.02509 0.01557 0.0061 1.0000 0.2080
-7.500 -0.8910 0.02468 0.01514 0.0079 1.0000 0.2120
-7.250 -0.8733 0.02423 0.01461 0.0096 1.0000 0.2164
-7.000 -0.8557 0.02376 0.01395 0.0114 1.0000 0.2210
-6.750 -0.8363 0.02334 0.01360 0.0129 1.0000 0.2246
-6.500 -0.8173 0.02296 0.01321 0.0144 1.0000 0.2289
-6.250 -0.7981 0.02257 0.01274 0.0160 1.0000 0.2335
-6.000 -0.7788 0.02218 0.01224 0.0175 1.0000 0.2380
-5.750 -0.7590 0.02181 0.01194 0.0189 1.0000 0.2420
-5.500 -0.7393 0.02149 0.01160 0.0203 1.0000 0.2467
-5.250 -0.7194 0.02118 0.01121 0.0217 1.0000 0.2518
-5.000 -0.6991 0.02085 0.01089 0.0230 1.0000 0.2560
-4.750 -0.6792 0.02057 0.01064 0.0244 1.0000 0.2606
-4.500 -0.6592 0.02032 0.01038 0.0257 1.0000 0.2659
-4.250 -0.6345 0.02008 0.01010 0.0261 0.9987 0.2715
-4.000 -0.5887 0.01988 0.00998 0.0223 0.9900 0.2782
-3.750 -0.5398 0.01972 0.00978 0.0180 0.9808 0.2869
-3.500 -0.4954 0.01939 0.00957 0.0147 0.9701 0.2944
-3.250 -0.4530 0.01911 0.00929 0.0118 0.9589 0.3031
-3.000 -0.4117 0.01876 0.00905 0.0093 0.9480 0.3113
-2.750 -0.3665 0.01845 0.00877 0.0061 0.9382 0.3220
-2.500 -0.3328 0.01805 0.00850 0.0051 0.9248 0.3311
-2.250 -0.2992 0.01769 0.00821 0.0043 0.9103 0.3415
-2.000 -0.2679 0.01731 0.00792 0.0040 0.8936 0.3534
-1.750 -0.2386 0.01691 0.00764 0.0041 0.8740 0.3659
-1.500 -0.2136 0.01655 0.00738 0.0052 0.8481 0.3795
-1.250 -0.1779 0.01611 0.00705 0.0042 0.8195 0.3974
-1.000 -0.1337 0.01564 0.00665 0.0018 0.7819 0.4214
-0.750 -0.0867 0.01521 0.00621 -0.0011 0.7279 0.4513
-0.500 -0.0512 0.01503 0.00593 -0.0019 0.6663 0.4836
-0.250 -0.0244 0.01498 0.00581 -0.0011 0.6103 0.5193
0.000 0.0000 0.01498 0.00578 0.0000 0.5612 0.5613
0.250 0.0244 0.01498 0.00581 0.0011 0.5192 0.6103
0.500 0.0512 0.01503 0.00593 0.0019 0.4835 0.6665
0.750 0.0868 0.01521 0.00622 0.0011 0.4512 0.7281
1.000 0.1339 0.01564 0.00665 -0.0018 0.4213 0.7822
1.250 0.1779 0.01612 0.00705 -0.0042 0.3972 0.8196
1.500 0.2135 0.01655 0.00738 -0.0051 0.3795 0.8480
1.750 0.2384 0.01691 0.00764 -0.0041 0.3660 0.8739
2.000 0.2678 0.01731 0.00792 -0.0040 0.3535 0.8936
2.250 0.2991 0.01769 0.00821 -0.0043 0.3416 0.9103
2.500 0.3327 0.01805 0.00850 -0.0051 0.3311 0.9248
2.750 0.3665 0.01844 0.00877 -0.0060 0.3220 0.9382
3.000 0.4117 0.01876 0.00905 -0.0093 0.3114 0.9481
3.250 0.4531 0.01911 0.00929 -0.0119 0.3030 0.9590
3.500 0.4956 0.01939 0.00957 -0.0147 0.2943 0.9702
3.750 0.5398 0.01971 0.00978 -0.0180 0.2869 0.9809
4.000 0.5888 0.01988 0.00998 -0.0223 0.2782 0.9901
4.250 0.6345 0.02008 0.01010 -0.0261 0.2716 0.9987
4.500 0.6590 0.02032 0.01037 -0.0257 0.2660 1.0000
4.750 0.6791 0.02057 0.01064 -0.0243 0.2606 1.0000
5.000 0.6990 0.02085 0.01088 -0.0230 0.2560 1.0000
5.250 0.7192 0.02118 0.01121 -0.0217 0.2518 1.0000
5.500 0.7392 0.02149 0.01160 -0.0203 0.2467 1.0000
5.750 0.7589 0.02181 0.01193 -0.0188 0.2420 1.0000
6.000 0.7787 0.02217 0.01224 -0.0174 0.2381 1.0000
6.250 0.7980 0.02257 0.01273 -0.0159 0.2336 1.0000
6.500 0.8172 0.02296 0.01321 -0.0144 0.2289 1.0000
6.750 0.8362 0.02333 0.01360 -0.0129 0.2247 1.0000
7.000 0.8556 0.02376 0.01395 -0.0114 0.2211 1.0000
7.250 0.8732 0.02422 0.01460 -0.0096 0.2164 1.0000
7.500 0.8910 0.02468 0.01515 -0.0078 0.2120 1.0000
7.750 0.9089 0.02508 0.01557 -0.0061 0.2080 1.0000
8.000 0.9271 0.02555 0.01600 -0.0045 0.2046 1.0000
8.250 0.9424 0.02610 0.01676 -0.0023 0.1999 1.0000
8.500 0.9583 0.02660 0.01736 -0.0003 0.1957 1.0000
8.750 0.9748 0.02702 0.01779 0.0016 0.1920 1.0000
9.000 0.9907 0.02752 0.01831 0.0036 0.1885 1.0000
9.250 1.0032 0.02817 0.01918 0.0061 0.1840 1.0000
9.500 1.0167 0.02870 0.01980 0.0084 0.1799 1.0000
9.750 1.0312 0.02911 0.02022 0.0106 0.1764 1.0000
10.000 1.0439 0.02968 0.02086 0.0130 0.1729 1.0000
10.250 1.0529 0.03043 0.02181 0.0159 0.1687 1.0000
10.500 1.0633 0.03098 0.02245 0.0186 0.1648 1.0000
10.750 1.0752 0.03140 0.02286 0.0211 0.1614 1.0000
11.000 1.0838 0.03209 0.02365 0.0240 0.1581 1.0000
11.250 1.0880 0.03295 0.02472 0.0273 0.1541 1.0000
11.500 1.0939 0.03359 0.02544 0.0304 0.1504 1.0000
11.750 1.1013 0.03408 0.02593 0.0334 0.1474 1.0000
12.000 1.1039 0.03481 0.02671 0.0369 0.1445 1.0000
12.250 1.0993 0.03595 0.02806 0.0409 0.1410 1.0000
12.500 1.0987 0.03693 0.02916 0.0442 0.1376 1.0000
12.750 1.1022 0.03775 0.03002 0.0468 0.1346 1.0000
13.000 1.1082 0.03855 0.03079 0.0489 0.1319 1.0000
13.250 1.0981 0.04059 0.03310 0.0516 0.1287 1.0000
13.500 1.0908 0.04258 0.03526 0.0536 0.1256 1.0000
13.750 1.0874 0.04437 0.03714 0.0549 0.1226 1.0000
14.000 1.0896 0.04584 0.03859 0.0558 0.1199 1.0000
14.250 1.0767 0.04902 0.04193 0.0561 0.1175 1.0000
14.500 1.0509 0.05406 0.04723 0.0549 0.1152 1.0000
14.750 1.0172 0.06089 0.05428 0.0518 0.1132 1.0000
15.000 0.7903 0.10170 0.09547 0.0280 0.1084 1.0000
15.250 0.8301 0.09752 0.09130 0.0309 0.1076 1.0000
15.500 0.9512 0.07950 0.07312 0.0423 0.1062 1.0000
16.500 0.7156 0.13950 0.13334 0.0104 0.0844 1.0000
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Polar data table (+)
Polar graphs
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