E475 (15.01%) (e475-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: E475 (15.01%) (e475-il) Reynolds number: 50,000 Max Cl/Cd: 24.1 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e475-il-50000-n5.txt Download as CSV file: xf-e475-il-50000-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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.000 -0.6402 0.09754 0.08844 -0.0246 1.0000 0.1762
-11.750 -0.6276 0.09611 0.08697 -0.0239 1.0000 0.1795
-11.500 -0.7778 0.07009 0.06104 -0.0393 1.0000 0.1896
-11.250 -0.7188 0.07492 0.06583 -0.0347 1.0000 0.1917
-11.000 -0.7036 0.07417 0.06506 -0.0335 1.0000 0.1951
-10.750 -0.8195 0.05969 0.05051 -0.0373 1.0000 0.1996
-10.500 -0.8841 0.05437 0.04504 -0.0317 1.0000 0.2018
-10.250 -0.9326 0.05011 0.04043 -0.0255 1.0000 0.2049
-10.000 -0.9075 0.04986 0.04027 -0.0246 1.0000 0.2085
-9.750 -0.9016 0.04861 0.03896 -0.0221 1.0000 0.2123
-9.500 -0.9092 0.04653 0.03668 -0.0184 1.0000 0.2165
-9.250 -0.9270 0.04387 0.03362 -0.0135 1.0000 0.2210
-9.000 -0.9046 0.04339 0.03322 -0.0124 1.0000 0.2247
-8.750 -0.8933 0.04237 0.03213 -0.0102 1.0000 0.2291
-8.500 -0.8909 0.04076 0.03028 -0.0071 1.0000 0.2339
-8.250 -0.8860 0.03924 0.02853 -0.0042 1.0000 0.2386
-8.000 -0.8674 0.03856 0.02789 -0.0026 1.0000 0.2428
-7.750 -0.8554 0.03753 0.02672 -0.0004 1.0000 0.2477
-7.500 -0.8492 0.03609 0.02495 0.0025 1.0000 0.2533
-7.250 -0.8306 0.03533 0.02423 0.0040 1.0000 0.2574
-7.000 -0.8138 0.03455 0.02341 0.0057 1.0000 0.2623
-6.750 -0.8012 0.03351 0.02215 0.0079 1.0000 0.2683
-6.500 -0.7846 0.03265 0.02121 0.0096 1.0000 0.2731
-6.250 -0.7658 0.03196 0.02052 0.0111 1.0000 0.2780
-6.000 -0.7496 0.03115 0.01955 0.0129 1.0000 0.2840
-5.750 -0.7322 0.03039 0.01870 0.0145 1.0000 0.2897
-5.500 -0.7126 0.02979 0.01812 0.0159 1.0000 0.2950
-5.250 -0.6946 0.02910 0.01731 0.0174 1.0000 0.3013
-5.000 -0.6754 0.02847 0.01664 0.0188 1.0000 0.3073
-4.750 -0.6556 0.02795 0.01613 0.0201 1.0000 0.3134
-4.500 -0.6368 0.02737 0.01542 0.0215 1.0000 0.3207
-4.250 -0.6159 0.02688 0.01501 0.0227 1.0000 0.3266
-4.000 -0.5959 0.02642 0.01453 0.0239 1.0000 0.3339
-3.750 -0.5756 0.02597 0.01408 0.0251 1.0000 0.3414
-3.500 -0.5550 0.02559 0.01375 0.0262 1.0000 0.3492
-3.250 -0.5344 0.02523 0.01336 0.0273 1.0000 0.3576
-3.000 -0.5134 0.02491 0.01313 0.0283 1.0000 0.3660
-2.750 -0.4928 0.02463 0.01288 0.0293 1.0000 0.3756
-2.500 -0.4722 0.02438 0.01270 0.0303 1.0000 0.3859
-2.250 -0.4390 0.02420 0.01263 0.0288 0.9946 0.3984
-2.000 -0.3827 0.02405 0.01261 0.0230 0.9779 0.4172
-1.750 -0.3302 0.02377 0.01249 0.0181 0.9596 0.4386
-1.500 -0.2797 0.02337 0.01231 0.0139 0.9407 0.4629
-1.250 -0.2352 0.02289 0.01208 0.0110 0.9197 0.4915
-1.000 -0.1980 0.02234 0.01181 0.0098 0.8946 0.5236
-0.750 -0.1637 0.02177 0.01156 0.0093 0.8667 0.5632
-0.500 -0.1279 0.02117 0.01134 0.0089 0.8357 0.6132
-0.250 -0.0785 0.02067 0.01127 0.0067 0.8001 0.6782
0.000 0.0000 0.02049 0.01133 0.0000 0.7502 0.7502
0.250 0.0785 0.02067 0.01126 -0.0067 0.6781 0.8000
0.500 0.1279 0.02117 0.01134 -0.0090 0.6130 0.8356
0.750 0.1637 0.02177 0.01155 -0.0093 0.5630 0.8667
1.000 0.1981 0.02234 0.01181 -0.0098 0.5235 0.8947
1.250 0.2352 0.02289 0.01208 -0.0110 0.4915 0.9197
1.500 0.2795 0.02337 0.01231 -0.0138 0.4630 0.9406
1.750 0.3301 0.02376 0.01249 -0.0181 0.4387 0.9596
2.000 0.3827 0.02405 0.01261 -0.0230 0.4172 0.9780
2.250 0.4390 0.02420 0.01263 -0.0288 0.3985 0.9946
2.500 0.4721 0.02438 0.01270 -0.0303 0.3859 1.0000
2.750 0.4927 0.02463 0.01287 -0.0293 0.3757 1.0000
3.000 0.5133 0.02491 0.01313 -0.0283 0.3660 1.0000
3.250 0.5343 0.02523 0.01336 -0.0273 0.3576 1.0000
3.500 0.5549 0.02559 0.01375 -0.0262 0.3491 1.0000
3.750 0.5755 0.02597 0.01407 -0.0251 0.3414 1.0000
4.000 0.5958 0.02642 0.01453 -0.0239 0.3340 1.0000
4.250 0.6158 0.02688 0.01500 -0.0226 0.3266 1.0000
4.500 0.6367 0.02737 0.01542 -0.0215 0.3207 1.0000
4.750 0.6555 0.02794 0.01613 -0.0201 0.3134 1.0000
5.000 0.6753 0.02847 0.01663 -0.0188 0.3072 1.0000
5.250 0.6946 0.02909 0.01731 -0.0174 0.3014 1.0000
5.500 0.7125 0.02979 0.01812 -0.0158 0.2951 1.0000
5.750 0.7321 0.03038 0.01869 -0.0145 0.2897 1.0000
6.000 0.7496 0.03115 0.01956 -0.0129 0.2841 1.0000
6.250 0.7657 0.03196 0.02052 -0.0111 0.2780 1.0000
6.500 0.7845 0.03265 0.02121 -0.0096 0.2731 1.0000
6.750 0.8011 0.03351 0.02214 -0.0079 0.2682 1.0000
7.000 0.8137 0.03455 0.02341 -0.0057 0.2624 1.0000
7.250 0.8305 0.03532 0.02422 -0.0039 0.2574 1.0000
7.500 0.8492 0.03609 0.02495 -0.0025 0.2533 1.0000
7.750 0.8554 0.03752 0.02671 0.0004 0.2478 1.0000
8.000 0.8674 0.03856 0.02790 0.0026 0.2428 1.0000
8.250 0.8858 0.03925 0.02854 0.0042 0.2386 1.0000
8.500 0.8909 0.04075 0.03027 0.0071 0.2339 1.0000
8.750 0.8934 0.04236 0.03212 0.0102 0.2291 1.0000
9.000 0.9046 0.04338 0.03322 0.0124 0.2248 1.0000
9.500 0.9092 0.04652 0.03667 0.0184 0.2165 1.0000
9.750 0.9017 0.04860 0.03895 0.0221 0.2123 1.0000
10.000 0.9082 0.04981 0.04022 0.0245 0.2084 1.0000
10.250 0.9325 0.05011 0.04043 0.0255 0.2048 1.0000
10.500 0.8846 0.05435 0.04501 0.0317 0.2018 1.0000
10.750 0.8202 0.05968 0.05050 0.0372 0.1995 1.0000
11.000 0.7081 0.07358 0.06447 0.0338 0.1951 1.0000
11.250 0.7212 0.07465 0.06556 0.0348 0.1918 1.0000
11.500 0.7877 0.06904 0.05998 0.0397 0.1895 1.0000
11.750 0.6283 0.09614 0.08701 0.0238 0.1796 1.0000
12.000 0.6421 0.09736 0.08826 0.0246 0.1762 1.0000
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Polar data table (+)
Polar graphs
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