E231 (e231-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: E231 (e231-il) Reynolds number: 100,000 Max Cl/Cd: 53.02 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e231-il-100000.txt Download as CSV file: xf-e231-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: E231
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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4348 0.10181 0.09755 -0.0419 1.0000 0.0921
-9.000 -0.4655 0.09997 0.09581 -0.0417 1.0000 0.0924
-8.750 -0.4918 0.09792 0.09383 -0.0409 1.0000 0.0925
-8.500 -0.5196 0.09638 0.09233 -0.0384 1.0000 0.0926
-8.250 -0.5500 0.09505 0.09101 -0.0349 1.0000 0.0926
-8.000 -0.5764 0.09319 0.08912 -0.0324 1.0000 0.0928
-7.750 -0.5410 0.08804 0.08415 -0.0297 1.0000 0.0964
-7.500 -0.5529 0.08587 0.08200 -0.0270 1.0000 0.0981
-7.250 -0.5681 0.08343 0.07956 -0.0247 1.0000 0.1000
-7.000 -0.5845 0.08077 0.07687 -0.0229 1.0000 0.1023
-6.750 -0.6205 0.07887 0.07464 -0.0214 1.0000 0.1064
-6.500 -0.6221 0.07428 0.07012 -0.0195 1.0000 0.1086
-6.250 -0.6164 0.07156 0.06746 -0.0173 1.0000 0.1110
-6.000 -0.6284 0.06932 0.06471 -0.0168 0.9980 0.1215
-5.750 -0.6062 0.06469 0.06031 -0.0169 0.9955 0.1256
-5.500 -0.5964 0.06131 0.05673 -0.0174 0.9916 0.1383
-5.250 -0.5842 0.05848 0.05368 -0.0177 0.9874 0.1514
-4.500 -0.5126 0.04141 0.03437 -0.0155 0.9770 0.0623
-4.250 -0.4832 0.03839 0.03039 -0.0141 0.9733 0.0523
-4.000 -0.4517 0.03509 0.02672 -0.0148 0.9703 0.0503
-3.750 -0.4294 0.03302 0.02432 -0.0136 0.9660 0.0485
-3.500 -0.3992 0.03103 0.02192 -0.0133 0.9619 0.0487
-3.250 -0.3637 0.02958 0.02017 -0.0141 0.9582 0.0501
-3.000 -0.3358 0.02827 0.01878 -0.0140 0.9540 0.0558
-2.750 -0.3108 0.02743 0.01791 -0.0134 0.9489 0.0647
-2.500 -0.2820 0.02628 0.01692 -0.0137 0.9447 0.0839
-2.250 -0.0092 0.02528 0.01890 -0.0529 0.9586 1.0000
-2.000 0.0100 0.02536 0.01876 -0.0526 0.9522 1.0000
-1.750 0.0360 0.02548 0.01868 -0.0534 0.9459 1.0000
-1.500 0.0610 0.02568 0.01871 -0.0540 0.9399 1.0000
-1.250 0.0819 0.02584 0.01873 -0.0538 0.9327 1.0000
-1.000 0.1124 0.02610 0.01883 -0.0552 0.9268 1.0000
-0.750 0.1296 0.02630 0.01891 -0.0542 0.9187 1.0000
-0.500 0.1594 0.02658 0.01907 -0.0553 0.9122 1.0000
-0.250 0.1800 0.02681 0.01921 -0.0548 0.9039 1.0000
0.000 0.2026 0.02710 0.01941 -0.0545 0.8961 1.0000
0.250 0.2333 0.02734 0.01957 -0.0557 0.8887 1.0000
0.500 0.2489 0.02764 0.01982 -0.0541 0.8792 1.0000
0.750 0.2918 0.02784 0.01994 -0.0572 0.8732 1.0000
1.000 0.3024 0.02812 0.02020 -0.0546 0.8623 1.0000
1.250 0.3281 0.02838 0.02042 -0.0546 0.8536 1.0000
1.500 0.3651 0.02847 0.02050 -0.0565 0.8458 1.0000
1.750 0.3799 0.02873 0.02074 -0.0545 0.8347 1.0000
2.000 0.4376 0.02858 0.02060 -0.0597 0.8299 1.0000
2.250 0.4487 0.02879 0.02082 -0.0568 0.8177 1.0000
2.500 0.4655 0.02896 0.02101 -0.0550 0.8063 1.0000
2.750 0.5309 0.02843 0.02055 -0.0611 0.8019 1.0000
3.000 0.5457 0.02850 0.02064 -0.0587 0.7895 1.0000
3.250 0.5660 0.02847 0.02066 -0.0571 0.7779 1.0000
3.500 0.6314 0.02741 0.01974 -0.0626 0.7737 1.0000
3.750 0.6502 0.02722 0.01961 -0.0605 0.7614 1.0000
4.000 0.6741 0.02683 0.01929 -0.0591 0.7497 1.0000
4.250 0.7335 0.02523 0.01786 -0.0627 0.7451 1.0000
4.500 0.7561 0.02465 0.01737 -0.0608 0.7325 1.0000
4.750 0.7809 0.02396 0.01678 -0.0592 0.7200 1.0000
5.000 0.8086 0.02311 0.01607 -0.0579 0.7073 1.0000
5.250 0.8387 0.02211 0.01519 -0.0569 0.6940 1.0000
5.500 0.8696 0.02108 0.01427 -0.0560 0.6791 1.0000
5.750 0.9029 0.01997 0.01326 -0.0554 0.6620 1.0000
6.000 0.9213 0.01945 0.01284 -0.0526 0.6387 1.0000
6.250 0.9439 0.01889 0.01232 -0.0505 0.6116 1.0000
6.500 0.9652 0.01851 0.01191 -0.0483 0.5785 1.0000
6.750 0.9803 0.01849 0.01179 -0.0453 0.5403 1.0000
7.000 0.9924 0.01872 0.01188 -0.0419 0.4998 1.0000
7.250 1.0006 0.01918 0.01212 -0.0381 0.4598 1.0000
7.500 1.0056 0.01979 0.01253 -0.0338 0.4224 1.0000
7.750 1.0087 0.02049 0.01303 -0.0295 0.3875 1.0000
8.000 1.0109 0.02123 0.01361 -0.0250 0.3554 1.0000
8.250 1.0133 0.02202 0.01424 -0.0208 0.3257 1.0000
8.500 1.0155 0.02286 0.01493 -0.0166 0.2981 1.0000
8.750 1.0183 0.02376 0.01567 -0.0126 0.2727 1.0000
9.000 1.0230 0.02474 0.01647 -0.0092 0.2488 1.0000
9.250 1.0271 0.02572 0.01745 -0.0058 0.2257 1.0000
9.500 1.0344 0.02687 0.01848 -0.0031 0.2042 1.0000
9.750 1.0414 0.02802 0.01959 -0.0004 0.1844 1.0000
10.000 1.0511 0.02929 0.02074 0.0017 0.1665 1.0000
10.250 1.0618 0.03066 0.02208 0.0037 0.1498 1.0000
10.500 1.0707 0.03202 0.02347 0.0058 0.1348 1.0000
10.750 1.0809 0.03350 0.02497 0.0077 0.1211 1.0000
11.000 1.0908 0.03505 0.02653 0.0095 0.1086 1.0000
11.250 1.1035 0.03679 0.02825 0.0109 0.0969 1.0000
11.500 1.1097 0.03833 0.02989 0.0129 0.0872 1.0000
11.750 1.1150 0.04026 0.03205 0.0150 0.0784 1.0000
12.000 1.1221 0.04239 0.03425 0.0167 0.0698 1.0000
12.250 1.1283 0.04429 0.03615 0.0183 0.0626 1.0000
12.500 1.1294 0.04697 0.03915 0.0204 0.0569 1.0000
12.750 1.1333 0.04928 0.04152 0.0220 0.0516 1.0000
13.000 1.1300 0.05250 0.04501 0.0239 0.0476 1.0000
13.250 1.1243 0.05538 0.04820 0.0258 0.0452 1.0000
13.500 1.1183 0.05835 0.05139 0.0273 0.0425 1.0000
13.750 1.1183 0.06162 0.05472 0.0282 0.0403 1.0000
14.000 1.1075 0.06676 0.06006 0.0290 0.0389 1.0000
14.250 1.0859 0.07062 0.06426 0.0298 0.0383 1.0000
14.500 1.0681 0.07507 0.06898 0.0298 0.0382 1.0000
14.750 1.0470 0.08019 0.07437 0.0291 0.0381 1.0000
15.000 1.0268 0.08578 0.08018 0.0276 0.0382 1.0000
15.250 1.0062 0.09183 0.08643 0.0255 0.0385 1.0000
15.500 0.9845 0.09867 0.09344 0.0226 0.0388 1.0000
15.750 0.9602 0.10622 0.10115 0.0186 0.0389 1.0000
16.000 0.7772 0.16830 0.16328 -0.0181 0.1007 1.0000
16.250 0.7919 0.17217 0.16721 -0.0172 0.0980 1.0000
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Polar data table (+)
Polar graphs
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