E475 (15.01%) (e475-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: E475 (15.01%) (e475-il) Reynolds number: 100,000 Max Cl/Cd: 30.54 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e475-il-100000.txt Download as CSV file: xf-e475-il-100000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.8180 0.06658 0.06037 -0.0421 1.0000 0.1913
-11.500 -0.8647 0.05995 0.05368 -0.0420 1.0000 0.1930
-11.250 -0.8963 0.05613 0.04979 -0.0391 1.0000 0.1952
-11.000 -0.9609 0.05127 0.04475 -0.0316 1.0000 0.1958
-10.750 -0.9802 0.04885 0.04218 -0.0269 1.0000 0.1990
-10.500 -1.0117 0.04564 0.03865 -0.0207 1.0000 0.2021
-10.250 -1.0416 0.04255 0.03511 -0.0139 1.0000 0.2054
-10.000 -1.0038 0.04278 0.03559 -0.0147 1.0000 0.2098
-9.750 -0.9919 0.04199 0.03475 -0.0123 1.0000 0.2144
-9.500 -1.0036 0.03980 0.03220 -0.0073 1.0000 0.2191
-9.250 -0.9987 0.03817 0.03041 -0.0042 1.0000 0.2231
-9.000 -0.9752 0.03786 0.03021 -0.0033 1.0000 0.2275
-8.750 -0.9668 0.03671 0.02890 -0.0004 1.0000 0.2325
-8.500 -0.9708 0.03492 0.02664 0.0040 1.0000 0.2375
-8.250 -0.9472 0.03418 0.02606 0.0048 1.0000 0.2417
-8.000 -0.9297 0.03350 0.02536 0.0065 1.0000 0.2467
-7.750 -0.9225 0.03223 0.02378 0.0096 1.0000 0.2522
-7.500 -0.9068 0.03113 0.02261 0.0114 1.0000 0.2567
-7.250 -0.8869 0.03050 0.02200 0.0128 1.0000 0.2615
-7.000 -0.8725 0.02961 0.02094 0.0150 1.0000 0.2672
-6.750 -0.8583 0.02855 0.01969 0.0171 1.0000 0.2724
-6.500 -0.8376 0.02791 0.01911 0.0183 1.0000 0.2771
-6.250 -0.8198 0.02720 0.01829 0.0200 1.0000 0.2827
-6.000 -0.8043 0.02635 0.01721 0.0220 1.0000 0.2885
-5.750 -0.7828 0.02572 0.01668 0.0231 1.0000 0.2934
-5.500 -0.7637 0.02512 0.01600 0.0246 1.0000 0.2993
-5.250 -0.7462 0.02443 0.01511 0.0263 1.0000 0.3052
-5.000 -0.7245 0.02387 0.01466 0.0273 1.0000 0.3106
-4.750 -0.7049 0.02338 0.01409 0.0287 1.0000 0.3170
-4.500 -0.6855 0.02281 0.01341 0.0301 1.0000 0.3231
-4.250 -0.6640 0.02235 0.01305 0.0311 1.0000 0.3287
-4.000 -0.6443 0.02197 0.01258 0.0324 1.0000 0.3360
-3.750 -0.6236 0.02152 0.01216 0.0335 1.0000 0.3425
-3.500 -0.6032 0.02118 0.01186 0.0347 1.0000 0.3495
-3.250 -0.5836 0.02084 0.01144 0.0360 1.0000 0.3569
-3.000 -0.5632 0.02050 0.01124 0.0370 1.0000 0.3640
-2.750 -0.5445 0.02029 0.01095 0.0383 1.0000 0.3729
-2.500 -0.5249 0.01998 0.01082 0.0394 1.0000 0.3806
-2.250 -0.5031 0.01985 0.01065 0.0399 0.9988 0.3906
-2.000 -0.4424 0.01990 0.01086 0.0332 0.9840 0.4069
-1.750 -0.3834 0.01977 0.01090 0.0270 0.9692 0.4253
-1.500 -0.3265 0.01940 0.01078 0.0215 0.9540 0.4459
-1.250 -0.2719 0.01886 0.01051 0.0167 0.9381 0.4721
-1.000 -0.2248 0.01815 0.01010 0.0136 0.9190 0.5029
-0.750 -0.1799 0.01733 0.00964 0.0112 0.8984 0.5456
-0.500 -0.1332 0.01631 0.00915 0.0090 0.8771 0.6078
-0.250 -0.0869 0.01533 0.00878 0.0075 0.8498 0.6999
0.000 0.0000 0.01497 0.00887 0.0000 0.8041 0.8042
0.250 0.0869 0.01533 0.00878 -0.0075 0.6998 0.8499
0.500 0.1333 0.01632 0.00915 -0.0090 0.6076 0.8772
0.750 0.1799 0.01734 0.00964 -0.0112 0.5454 0.8985
1.000 0.2248 0.01816 0.01011 -0.0136 0.5029 0.9191
1.250 0.2719 0.01886 0.01051 -0.0166 0.4721 0.9381
1.500 0.3263 0.01939 0.01078 -0.0214 0.4459 0.9540
1.750 0.3832 0.01977 0.01090 -0.0270 0.4254 0.9692
2.000 0.4423 0.01990 0.01086 -0.0332 0.4070 0.9840
2.250 0.5032 0.01984 0.01064 -0.0399 0.3906 0.9989
2.500 0.5247 0.01997 0.01082 -0.0394 0.3806 1.0000
2.750 0.5444 0.02029 0.01095 -0.0383 0.3730 1.0000
3.000 0.5630 0.02050 0.01124 -0.0370 0.3640 1.0000
3.250 0.5835 0.02084 0.01144 -0.0359 0.3569 1.0000
3.500 0.6031 0.02118 0.01186 -0.0347 0.3494 1.0000
3.750 0.6235 0.02151 0.01216 -0.0335 0.3425 1.0000
4.000 0.6442 0.02197 0.01257 -0.0324 0.3359 1.0000
4.250 0.6639 0.02235 0.01305 -0.0311 0.3288 1.0000
4.500 0.6853 0.02281 0.01341 -0.0300 0.3231 1.0000
4.750 0.7048 0.02338 0.01409 -0.0287 0.3171 1.0000
5.000 0.7244 0.02386 0.01465 -0.0273 0.3105 1.0000
5.250 0.7461 0.02443 0.01510 -0.0262 0.3052 1.0000
5.500 0.7636 0.02512 0.01600 -0.0246 0.2993 1.0000
5.750 0.7827 0.02572 0.01668 -0.0231 0.2935 1.0000
6.000 0.8041 0.02634 0.01720 -0.0220 0.2885 1.0000
6.250 0.8197 0.02719 0.01828 -0.0200 0.2828 1.0000
6.500 0.8375 0.02791 0.01910 -0.0183 0.2771 1.0000
6.750 0.8582 0.02854 0.01968 -0.0171 0.2723 1.0000
7.000 0.8724 0.02960 0.02093 -0.0150 0.2672 1.0000
7.250 0.8867 0.03049 0.02200 -0.0128 0.2615 1.0000
7.500 0.9067 0.03112 0.02260 -0.0114 0.2567 1.0000
7.750 0.9225 0.03222 0.02377 -0.0096 0.2522 1.0000
8.000 0.9296 0.03349 0.02535 -0.0065 0.2467 1.0000
8.250 0.9471 0.03417 0.02605 -0.0048 0.2418 1.0000
8.500 0.9706 0.03492 0.02664 -0.0040 0.2375 1.0000
8.750 0.9668 0.03671 0.02890 0.0004 0.2326 1.0000
9.000 0.9750 0.03787 0.03021 0.0033 0.2276 1.0000
9.250 0.9987 0.03816 0.03040 0.0042 0.2231 1.0000
9.500 1.0033 0.03979 0.03220 0.0073 0.2190 1.0000
9.750 0.9919 0.04198 0.03475 0.0123 0.2145 1.0000
10.000 1.0041 0.04275 0.03556 0.0146 0.2098 1.0000
10.250 1.0424 0.04251 0.03505 0.0138 0.2053 1.0000
10.500 1.0119 0.04560 0.03861 0.0207 0.2021 1.0000
10.750 0.9805 0.04884 0.04216 0.0269 0.1990 1.0000
11.000 0.9614 0.05125 0.04473 0.0315 0.1957 1.0000
11.250 0.8887 0.05662 0.05029 0.0394 0.1954 1.0000
11.500 0.8649 0.05999 0.05372 0.0419 0.1930 1.0000
11.750 0.8209 0.06637 0.06016 0.0421 0.1913 1.0000
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Polar data table (+)
Polar graphs
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