E10(08%) (e228-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: E10(08%) (e228-il) Reynolds number: 100,000 Max Cl/Cd: 39.51 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e228-il-100000.txt Download as CSV file: xf-e228-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: E10(08%)
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
------ -------- --------- --------- -------- -------- --------
-10.000 -0.6171 0.07640 0.07206 -0.0140 1.0000 0.0719
-9.750 -0.7246 0.07574 0.07111 -0.0188 1.0000 0.0717
-9.500 -0.7859 0.06637 0.06135 -0.0215 1.0000 0.0601
-9.250 -0.7936 0.06161 0.05646 -0.0211 1.0000 0.0592
-9.000 -0.8021 0.05704 0.05164 -0.0202 1.0000 0.0587
-8.750 -0.8054 0.05239 0.04670 -0.0191 1.0000 0.0576
-8.500 -0.8061 0.04793 0.04185 -0.0175 1.0000 0.0570
-8.250 -0.8025 0.04366 0.03711 -0.0158 1.0000 0.0565
-8.000 -0.7949 0.03947 0.03239 -0.0138 1.0000 0.0557
-7.750 -0.7824 0.03584 0.02823 -0.0120 1.0000 0.0556
-7.500 -0.7657 0.03278 0.02470 -0.0103 1.0000 0.0565
-7.250 -0.7466 0.03068 0.02212 -0.0088 1.0000 0.0599
-7.000 -0.7252 0.02797 0.01913 -0.0077 1.0000 0.0631
-6.750 -0.7018 0.02586 0.01698 -0.0068 1.0000 0.0670
-6.500 -0.6781 0.02424 0.01511 -0.0057 1.0000 0.0727
-6.250 -0.6564 0.02253 0.01350 -0.0047 1.0000 0.0817
-6.000 -0.6358 0.02088 0.01191 -0.0033 1.0000 0.0935
-5.750 -0.6184 0.01926 0.01048 -0.0014 1.0000 0.1197
-5.500 -0.6043 0.01766 0.00928 0.0009 1.0000 0.1823
-5.250 -0.5893 0.01659 0.00860 0.0029 1.0000 0.2460
-5.000 -0.5737 0.01593 0.00818 0.0049 1.0000 0.3100
-4.750 -0.5585 0.01535 0.00782 0.0071 1.0000 0.3678
-4.500 -0.5426 0.01480 0.00749 0.0094 1.0000 0.4189
-4.250 -0.5265 0.01433 0.00719 0.0117 1.0000 0.4696
-4.000 -0.5104 0.01391 0.00697 0.0141 1.0000 0.5190
-3.750 -0.4943 0.01357 0.00678 0.0165 1.0000 0.5690
-3.500 -0.4780 0.01328 0.00664 0.0191 1.0000 0.6171
-3.250 -0.4615 0.01305 0.00656 0.0216 1.0000 0.6655
-3.000 -0.4446 0.01290 0.00654 0.0242 1.0000 0.7132
-2.750 -0.4266 0.01284 0.00659 0.0268 1.0000 0.7596
-2.500 -0.4065 0.01288 0.00671 0.0290 1.0000 0.8062
-2.250 -0.3810 0.01306 0.00689 0.0303 1.0000 0.8517
-2.000 -0.3421 0.01342 0.00719 0.0290 1.0000 0.8929
-1.750 -0.2891 0.01389 0.00753 0.0249 1.0000 0.9265
-1.500 -0.2175 0.01434 0.00779 0.0169 1.0000 0.9476
-1.250 -0.1482 0.01457 0.00788 0.0089 1.0000 0.9673
-1.000 -0.0780 0.01458 0.00777 0.0002 1.0000 0.9845
-0.750 -0.0043 0.01435 0.00745 -0.0094 1.0000 0.9997
-0.500 -0.0339 0.01443 0.00752 -0.0027 1.0000 1.0000
-0.250 0.0285 0.01447 0.00753 -0.0105 0.9862 1.0000
0.000 0.0918 0.01444 0.00748 -0.0181 0.9727 1.0000
0.250 0.1565 0.01431 0.00737 -0.0257 0.9596 1.0000
0.500 0.2157 0.01408 0.00718 -0.0320 0.9437 1.0000
0.750 0.2600 0.01389 0.00703 -0.0352 0.9219 1.0000
1.000 0.2930 0.01373 0.00688 -0.0359 0.8989 1.0000
1.250 0.3131 0.01367 0.00681 -0.0340 0.8732 1.0000
1.500 0.3296 0.01363 0.00676 -0.0313 0.8480 1.0000
1.750 0.3456 0.01360 0.00671 -0.0284 0.8240 1.0000
2.000 0.3621 0.01357 0.00665 -0.0256 0.8007 1.0000
2.250 0.3793 0.01358 0.00664 -0.0230 0.7759 1.0000
2.500 0.3973 0.01360 0.00662 -0.0205 0.7517 1.0000
2.750 0.4160 0.01361 0.00660 -0.0180 0.7276 1.0000
3.000 0.4355 0.01367 0.00663 -0.0159 0.7007 1.0000
3.250 0.4556 0.01374 0.00667 -0.0138 0.6730 1.0000
3.500 0.4760 0.01384 0.00672 -0.0119 0.6442 1.0000
3.750 0.4967 0.01397 0.00680 -0.0100 0.6142 1.0000
4.000 0.5177 0.01414 0.00691 -0.0082 0.5822 1.0000
4.250 0.5387 0.01435 0.00707 -0.0065 0.5476 1.0000
4.500 0.5597 0.01460 0.00722 -0.0048 0.5127 1.0000
4.750 0.5805 0.01490 0.00746 -0.0033 0.4734 1.0000
5.000 0.6011 0.01527 0.00776 -0.0017 0.4323 1.0000
5.250 0.6211 0.01572 0.00809 -0.0001 0.3884 1.0000
5.500 0.6404 0.01629 0.00847 0.0014 0.3420 1.0000
5.750 0.6592 0.01698 0.00900 0.0030 0.2918 1.0000
6.000 0.6769 0.01787 0.00964 0.0046 0.2435 1.0000
6.250 0.6940 0.01894 0.01048 0.0062 0.1993 1.0000
6.500 0.7115 0.02011 0.01149 0.0078 0.1619 1.0000
6.750 0.7288 0.02142 0.01263 0.0094 0.1330 1.0000
7.000 0.7467 0.02283 0.01399 0.0110 0.1097 1.0000
7.250 0.7646 0.02441 0.01542 0.0124 0.0919 1.0000
7.500 0.7834 0.02636 0.01729 0.0137 0.0778 1.0000
7.750 0.8020 0.02777 0.01886 0.0152 0.0667 1.0000
8.000 0.8218 0.03024 0.02165 0.0167 0.0601 1.0000
8.250 0.8398 0.03233 0.02371 0.0178 0.0536 1.0000
8.500 0.8553 0.03516 0.02700 0.0195 0.0506 1.0000
8.750 0.8680 0.03825 0.03059 0.0215 0.0490 1.0000
9.000 0.8764 0.04172 0.03455 0.0235 0.0482 1.0000
9.250 0.8796 0.04558 0.03888 0.0256 0.0481 1.0000
9.500 0.8777 0.04960 0.04333 0.0276 0.0484 1.0000
9.750 0.8700 0.05362 0.04772 0.0295 0.0483 1.0000
10.000 0.8572 0.05759 0.05199 0.0312 0.0484 1.0000
10.250 0.8377 0.06143 0.05604 0.0329 0.0489 1.0000
10.500 0.8185 0.06570 0.06044 0.0332 0.0502 1.0000
10.750 0.7974 0.07048 0.06534 0.0317 0.0507 1.0000
11.000 0.7764 0.07627 0.07121 0.0285 0.0513 1.0000
11.250 0.7646 0.08224 0.07720 0.0259 0.0523 1.0000
|
Polar data table (+)
Polar graphs
<< Back to E10(08%) (e228-il)