E222 (10.17%) (e222-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: E222 (10.17%) (e222-il) Reynolds number: 200,000 Max Cl/Cd: 71.32 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e222-il-200000-n5.txt Download as CSV file: xf-e222-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: E222 (10.17%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.4647 0.08707 0.08345 -0.0385 1.0000 0.0187
-9.500 -0.4733 0.08188 0.07832 -0.0405 1.0000 0.0184
-9.250 -0.4866 0.07590 0.07240 -0.0428 1.0000 0.0180
-9.000 -0.5089 0.06809 0.06468 -0.0464 1.0000 0.0175
-8.750 -0.5606 0.05584 0.05241 -0.0543 1.0000 0.0169
-8.500 -0.5931 0.04908 0.04540 -0.0558 1.0000 0.0166
-8.250 -0.6137 0.04310 0.03900 -0.0555 1.0000 0.0163
-8.000 -0.6199 0.03830 0.03373 -0.0546 1.0000 0.0160
-7.750 -0.6000 0.03368 0.02855 -0.0573 0.9967 0.0160
-7.500 -0.5733 0.03020 0.02457 -0.0598 0.9933 0.0160
-7.250 -0.5458 0.02753 0.02148 -0.0615 0.9895 0.0162
-7.000 -0.5159 0.02531 0.01890 -0.0632 0.9862 0.0164
-6.750 -0.4840 0.02348 0.01678 -0.0649 0.9836 0.0169
-6.500 -0.4557 0.02197 0.01501 -0.0657 0.9793 0.0172
-6.250 -0.4251 0.02063 0.01348 -0.0667 0.9754 0.0177
-6.000 -0.3925 0.01948 0.01216 -0.0681 0.9724 0.0183
-5.750 -0.3614 0.01860 0.01115 -0.0691 0.9685 0.0196
-5.500 -0.3318 0.01776 0.01019 -0.0698 0.9635 0.0203
-5.250 -0.2988 0.01687 0.00918 -0.0711 0.9600 0.0207
-5.000 -0.2654 0.01589 0.00812 -0.0726 0.9568 0.0215
-4.750 -0.2370 0.01520 0.00735 -0.0730 0.9505 0.0226
-4.500 -0.2029 0.01461 0.00667 -0.0744 0.9466 0.0242
-4.250 -0.1666 0.01410 0.00604 -0.0763 0.9439 0.0267
-4.000 -0.1386 0.01362 0.00553 -0.0763 0.9366 0.0315
-3.750 -0.1043 0.01290 0.00500 -0.0780 0.9326 0.0675
-3.500 -0.0699 0.01223 0.00461 -0.0797 0.9287 0.1341
-3.250 -0.0404 0.01173 0.00433 -0.0803 0.9214 0.1961
-3.000 -0.0054 0.01128 0.00407 -0.0820 0.9169 0.2562
-2.750 0.0241 0.01082 0.00391 -0.0826 0.9090 0.3356
-2.500 0.0576 0.01039 0.00375 -0.0839 0.9031 0.4176
-2.250 0.0879 0.01014 0.00362 -0.0843 0.8947 0.4650
-2.000 0.1220 0.00990 0.00346 -0.0855 0.8879 0.5075
-1.750 0.1515 0.00972 0.00336 -0.0856 0.8780 0.5473
-1.500 0.1826 0.00954 0.00326 -0.0861 0.8688 0.5860
-1.250 0.2139 0.00939 0.00316 -0.0866 0.8592 0.6230
-1.000 0.2423 0.00928 0.00311 -0.0864 0.8475 0.6566
-0.750 0.2707 0.00918 0.00306 -0.0862 0.8356 0.6894
-0.500 0.2986 0.00911 0.00303 -0.0858 0.8233 0.7207
-0.250 0.3258 0.00906 0.00300 -0.0854 0.8103 0.7500
0.000 0.3523 0.00903 0.00299 -0.0847 0.7967 0.7776
0.250 0.3780 0.00901 0.00298 -0.0838 0.7824 0.8044
0.500 0.4030 0.00901 0.00298 -0.0828 0.7674 0.8311
0.750 0.4273 0.00902 0.00298 -0.0816 0.7521 0.8578
1.000 0.4514 0.00903 0.00298 -0.0804 0.7363 0.8839
1.250 0.4765 0.00905 0.00296 -0.0795 0.7200 0.9106
1.500 0.5048 0.00908 0.00296 -0.0792 0.7031 0.9384
1.750 0.5389 0.00913 0.00294 -0.0804 0.6849 0.9681
2.000 0.5718 0.00921 0.00295 -0.0815 0.6652 1.0000
2.250 0.5977 0.00936 0.00303 -0.0811 0.6459 1.0000
2.500 0.6235 0.00954 0.00311 -0.0807 0.6264 1.0000
2.750 0.6491 0.00971 0.00321 -0.0802 0.6059 1.0000
3.000 0.6745 0.00992 0.00333 -0.0797 0.5849 1.0000
3.250 0.6998 0.01013 0.00348 -0.0792 0.5628 1.0000
3.500 0.7246 0.01037 0.00364 -0.0786 0.5397 1.0000
3.750 0.7493 0.01062 0.00381 -0.0780 0.5157 1.0000
4.000 0.7738 0.01089 0.00401 -0.0773 0.4908 1.0000
4.250 0.7979 0.01119 0.00424 -0.0766 0.4651 1.0000
4.500 0.8216 0.01152 0.00448 -0.0759 0.4385 1.0000
4.750 0.8451 0.01187 0.00475 -0.0751 0.4106 1.0000
5.000 0.8683 0.01225 0.00504 -0.0743 0.3823 1.0000
5.250 0.8912 0.01265 0.00536 -0.0735 0.3537 1.0000
5.500 0.9139 0.01309 0.00573 -0.0727 0.3240 1.0000
5.750 0.9361 0.01357 0.00611 -0.0718 0.2931 1.0000
6.000 0.9579 0.01409 0.00653 -0.0709 0.2613 1.0000
6.250 0.9794 0.01464 0.00699 -0.0700 0.2310 1.0000
6.500 0.9998 0.01530 0.00751 -0.0689 0.1968 1.0000
6.750 1.0192 0.01607 0.00808 -0.0678 0.1575 1.0000
7.000 1.0386 0.01684 0.00868 -0.0667 0.1246 1.0000
7.250 1.0587 0.01756 0.00931 -0.0656 0.1020 1.0000
7.500 1.0779 0.01834 0.00998 -0.0645 0.0785 1.0000
7.750 1.0967 0.01914 0.01070 -0.0633 0.0581 1.0000
8.000 1.1143 0.02006 0.01154 -0.0619 0.0393 1.0000
8.250 1.1300 0.02113 0.01251 -0.0603 0.0237 1.0000
8.500 1.1461 0.02214 0.01354 -0.0586 0.0171 1.0000
8.750 1.1626 0.02306 0.01456 -0.0570 0.0147 1.0000
9.000 1.1773 0.02409 0.01567 -0.0552 0.0133 1.0000
9.250 1.1897 0.02515 0.01685 -0.0530 0.0125 1.0000
9.500 1.2014 0.02618 0.01802 -0.0507 0.0120 1.0000
9.750 1.2113 0.02732 0.01933 -0.0483 0.0115 1.0000
10.000 1.2201 0.02854 0.02069 -0.0459 0.0110 1.0000
10.250 1.2281 0.02983 0.02210 -0.0436 0.0105 1.0000
10.500 1.2352 0.03120 0.02359 -0.0414 0.0101 1.0000
10.750 1.2406 0.03274 0.02524 -0.0392 0.0096 1.0000
11.000 1.2411 0.03475 0.02735 -0.0368 0.0092 1.0000
11.250 1.2436 0.03671 0.02944 -0.0349 0.0089 1.0000
11.500 1.2471 0.03868 0.03157 -0.0332 0.0088 1.0000
11.750 1.2496 0.04085 0.03391 -0.0317 0.0086 1.0000
12.000 1.2515 0.04319 0.03642 -0.0305 0.0085 1.0000
12.250 1.2523 0.04577 0.03916 -0.0295 0.0084 1.0000
12.500 1.2522 0.04854 0.04214 -0.0287 0.0083 1.0000
12.750 1.2508 0.05160 0.04539 -0.0282 0.0081 1.0000
13.000 1.2486 0.05489 0.04887 -0.0280 0.0081 1.0000
13.250 1.2447 0.05853 0.05270 -0.0281 0.0080 1.0000
13.500 1.2393 0.06250 0.05688 -0.0287 0.0079 1.0000
13.750 1.2325 0.06686 0.06145 -0.0297 0.0079 1.0000
14.000 1.2240 0.07165 0.06644 -0.0311 0.0079 1.0000
14.250 1.2140 0.07692 0.07193 -0.0331 0.0078 1.0000
14.500 1.2025 0.08275 0.07796 -0.0357 0.0078 1.0000
14.750 1.1898 0.08910 0.08453 -0.0389 0.0078 1.0000
15.000 1.1755 0.09613 0.09176 -0.0427 0.0078 1.0000
15.250 1.1606 0.10366 0.09949 -0.0470 0.0078 1.0000
15.500 1.1445 0.11186 0.10787 -0.0520 0.0079 1.0000
15.750 1.1272 0.12081 0.11702 -0.0575 0.0079 1.0000
16.000 1.1090 0.13051 0.12689 -0.0636 0.0080 1.0000
16.250 1.0893 0.14112 0.13767 -0.0704 0.0081 1.0000
16.500 1.0669 0.15329 0.14999 -0.0780 0.0082 1.0000
16.750 1.0390 0.16832 0.16512 -0.0870 0.0085 1.0000
|
Polar data table (+)
Polar graphs
<< Back to E222 (10.17%) (e222-il)