E474 (14.09%) (e474-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: E474 (14.09%) (e474-il) Reynolds number: 50,000 Max Cl/Cd: 22.93 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e474-il-50000-n5.txt Download as CSV file: xf-e474-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: E474 (14.09%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.6577 0.09675 0.08782 -0.0134 1.0000 0.1707
-11.250 -0.6547 0.09365 0.08469 -0.0140 1.0000 0.1749
-11.000 -0.7671 0.07194 0.06308 -0.0282 1.0000 0.1829
-10.750 -0.7201 0.07590 0.06701 -0.0235 1.0000 0.1853
-10.500 -0.7528 0.06811 0.05921 -0.0275 1.0000 0.1902
-10.250 -0.8527 0.05699 0.04796 -0.0280 1.0000 0.1932
-10.000 -0.9078 0.05093 0.04153 -0.0241 1.0000 0.1968
-9.750 -0.8861 0.05040 0.04102 -0.0230 1.0000 0.2004
-9.500 -0.8763 0.04903 0.03958 -0.0213 1.0000 0.2044
-9.250 -0.8815 0.04652 0.03683 -0.0188 1.0000 0.2092
-9.000 -0.8863 0.04395 0.03395 -0.0160 1.0000 0.2139
-8.750 -0.8656 0.04333 0.03337 -0.0148 1.0000 0.2178
-8.500 -0.8552 0.04191 0.03180 -0.0129 1.0000 0.2225
-8.250 -0.8547 0.03974 0.02923 -0.0101 1.0000 0.2282
-8.000 -0.8355 0.03891 0.02843 -0.0088 1.0000 0.2322
-7.750 -0.8190 0.03798 0.02744 -0.0072 1.0000 0.2369
-7.500 -0.8086 0.03650 0.02570 -0.0051 1.0000 0.2424
-7.250 -0.7936 0.03533 0.02439 -0.0034 1.0000 0.2472
-7.000 -0.7742 0.03459 0.02365 -0.0020 1.0000 0.2519
-6.750 -0.7590 0.03351 0.02240 -0.0003 1.0000 0.2577
-6.500 -0.7432 0.03242 0.02113 0.0013 1.0000 0.2630
-6.250 -0.7227 0.03173 0.02046 0.0026 1.0000 0.2676
-6.000 -0.7049 0.03087 0.01948 0.0041 1.0000 0.2736
-5.750 -0.6873 0.02997 0.01843 0.0057 1.0000 0.2795
-5.500 -0.6665 0.02933 0.01784 0.0069 1.0000 0.2844
-5.250 -0.6474 0.02859 0.01698 0.0083 1.0000 0.2906
-5.000 -0.6279 0.02787 0.01618 0.0096 1.0000 0.2967
-4.750 -0.6071 0.02730 0.01565 0.0108 1.0000 0.3025
-4.500 -0.5873 0.02666 0.01488 0.0121 1.0000 0.3094
-4.250 -0.5662 0.02610 0.01436 0.0133 1.0000 0.3153
-4.000 -0.5454 0.02559 0.01386 0.0145 1.0000 0.3222
-3.750 -0.5248 0.02507 0.01328 0.0156 1.0000 0.3297
-3.500 -0.5035 0.02463 0.01292 0.0168 1.0000 0.3365
-3.250 -0.4827 0.02419 0.01241 0.0178 1.0000 0.3450
-3.000 -0.4613 0.02380 0.01216 0.0189 1.0000 0.3523
-2.500 -0.4192 0.02313 0.01160 0.0210 1.0000 0.3703
-2.250 -0.3983 0.02285 0.01136 0.0219 1.0000 0.3805
-2.000 -0.3565 0.02263 0.01124 0.0189 0.9888 0.3947
-1.750 -0.2990 0.02236 0.01113 0.0130 0.9677 0.4134
-1.500 -0.2493 0.02195 0.01092 0.0090 0.9428 0.4329
-1.250 -0.2037 0.02147 0.01066 0.0060 0.9147 0.4558
-1.000 -0.1636 0.02096 0.01037 0.0042 0.8804 0.4823
-0.750 -0.1238 0.02040 0.01006 0.0028 0.8400 0.5143
-0.500 -0.0809 0.01982 0.00974 0.0012 0.7908 0.5554
-0.250 -0.0377 0.01936 0.00944 0.0000 0.7313 0.6073
0.000 0.0000 0.01919 0.00931 0.0000 0.6677 0.6676
0.250 0.0377 0.01936 0.00945 0.0000 0.6073 0.7313
0.500 0.0810 0.01983 0.00975 -0.0012 0.5552 0.7909
0.750 0.1238 0.02040 0.01007 -0.0028 0.5143 0.8400
1.000 0.1636 0.02096 0.01037 -0.0042 0.4823 0.8805
1.250 0.2038 0.02147 0.01066 -0.0060 0.4559 0.9147
1.500 0.2493 0.02195 0.01091 -0.0090 0.4330 0.9428
1.750 0.2989 0.02236 0.01113 -0.0130 0.4134 0.9677
2.000 0.3565 0.02263 0.01123 -0.0189 0.3949 0.9888
2.250 0.3982 0.02285 0.01136 -0.0219 0.3804 1.0000
2.500 0.4191 0.02313 0.01160 -0.0210 0.3703 1.0000
3.000 0.4612 0.02380 0.01216 -0.0189 0.3523 1.0000
3.250 0.4826 0.02419 0.01240 -0.0178 0.3450 1.0000
3.500 0.5035 0.02463 0.01292 -0.0167 0.3365 1.0000
3.750 0.5247 0.02507 0.01328 -0.0156 0.3297 1.0000
4.000 0.5454 0.02559 0.01386 -0.0145 0.3222 1.0000
4.250 0.5662 0.02610 0.01436 -0.0133 0.3153 1.0000
4.500 0.5872 0.02666 0.01488 -0.0121 0.3095 1.0000
4.750 0.6070 0.02730 0.01565 -0.0108 0.3025 1.0000
5.000 0.6278 0.02787 0.01617 -0.0096 0.2967 1.0000
5.250 0.6473 0.02859 0.01698 -0.0083 0.2906 1.0000
5.500 0.6665 0.02933 0.01783 -0.0069 0.2845 1.0000
5.750 0.6872 0.02997 0.01843 -0.0056 0.2795 1.0000
6.000 0.7049 0.03087 0.01948 -0.0041 0.2736 1.0000
6.250 0.7227 0.03173 0.02046 -0.0026 0.2676 1.0000
6.500 0.7431 0.03242 0.02112 -0.0013 0.2630 1.0000
6.750 0.7590 0.03352 0.02240 0.0003 0.2577 1.0000
7.000 0.7742 0.03459 0.02365 0.0020 0.2519 1.0000
7.250 0.7936 0.03534 0.02439 0.0034 0.2472 1.0000
7.500 0.8086 0.03650 0.02570 0.0051 0.2424 1.0000
7.750 0.8190 0.03798 0.02744 0.0072 0.2369 1.0000
8.000 0.8355 0.03892 0.02844 0.0088 0.2323 1.0000
8.250 0.8546 0.03974 0.02923 0.0102 0.2281 1.0000
8.500 0.8553 0.04191 0.03180 0.0129 0.2225 1.0000
8.750 0.8655 0.04335 0.03339 0.0148 0.2179 1.0000
9.000 0.8862 0.04396 0.03396 0.0160 0.2139 1.0000
9.250 0.8817 0.04651 0.03681 0.0187 0.2092 1.0000
9.500 0.8765 0.04903 0.03958 0.0213 0.2044 1.0000
9.750 0.8866 0.05036 0.04098 0.0230 0.2004 1.0000
10.000 0.9078 0.05095 0.04155 0.0241 0.1968 1.0000
10.250 0.8533 0.05698 0.04795 0.0279 0.1932 1.0000
10.500 0.7552 0.06786 0.05896 0.0275 0.1901 1.0000
10.750 0.7247 0.07522 0.06633 0.0240 0.1853 1.0000
11.000 0.7684 0.07185 0.06299 0.0282 0.1829 1.0000
11.250 0.6559 0.09358 0.08463 0.0140 0.1748 1.0000
11.500 0.6588 0.09671 0.08778 0.0133 0.1707 1.0000
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Polar data table (+)
Polar graphs
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