E224 (10.17%) (e224-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: E224 (10.17%) (e224-il) Reynolds number: 1,000,000 Max Cl/Cd: 102.87 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e224-il-1000000.txt Download as CSV file: xf-e224-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: E224 (10.17%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.6541 0.05834 0.05658 -0.0462 1.0000 0.0071
-10.500 -0.6767 0.04866 0.04674 -0.0561 1.0000 0.0072
-10.250 -0.6979 0.04343 0.04137 -0.0602 1.0000 0.0070
-10.000 -0.7235 0.04048 0.03829 -0.0580 1.0000 0.0070
-9.750 -0.7447 0.03665 0.03424 -0.0553 1.0000 0.0069
-9.500 -0.7657 0.03210 0.02933 -0.0516 1.0000 0.0067
-9.250 -0.7709 0.02906 0.02599 -0.0483 1.0000 0.0066
-9.000 -0.7781 0.02514 0.02164 -0.0445 1.0000 0.0064
-8.750 -0.7581 0.02199 0.01809 -0.0450 0.9985 0.0063
-8.500 -0.7296 0.01982 0.01564 -0.0465 0.9966 0.0064
-8.250 -0.6983 0.01856 0.01422 -0.0481 0.9950 0.0066
-8.000 -0.6677 0.01730 0.01280 -0.0494 0.9933 0.0068
-7.750 -0.6387 0.01596 0.01130 -0.0502 0.9907 0.0070
-7.500 -0.6083 0.01469 0.00987 -0.0513 0.9884 0.0070
-7.250 -0.5763 0.01369 0.00874 -0.0526 0.9864 0.0072
-7.000 -0.5428 0.01292 0.00788 -0.0541 0.9849 0.0076
-6.750 -0.5094 0.01186 0.00668 -0.0557 0.9836 0.0082
-6.500 -0.4806 0.01110 0.00585 -0.0562 0.9797 0.0088
-6.250 -0.4484 0.01059 0.00528 -0.0573 0.9766 0.0094
-6.000 -0.4144 0.01016 0.00482 -0.0587 0.9744 0.0102
-5.750 -0.3804 0.00976 0.00437 -0.0601 0.9720 0.0110
-5.500 -0.3495 0.00920 0.00376 -0.0608 0.9682 0.0133
-5.250 -0.3212 0.00884 0.00338 -0.0609 0.9618 0.0173
-5.000 -0.2903 0.00838 0.00296 -0.0616 0.9571 0.0284
-4.750 -0.2633 0.00799 0.00266 -0.0615 0.9489 0.0482
-4.500 -0.2340 0.00764 0.00239 -0.0619 0.9421 0.0729
-4.250 -0.2075 0.00733 0.00217 -0.0616 0.9320 0.1004
-4.000 -0.1806 0.00700 0.00196 -0.0615 0.9223 0.1374
-3.750 -0.1538 0.00671 0.00178 -0.0613 0.9122 0.1786
-3.500 -0.1274 0.00644 0.00163 -0.0611 0.9010 0.2205
-3.250 -0.1006 0.00624 0.00150 -0.0608 0.8898 0.2558
-3.000 -0.0739 0.00602 0.00138 -0.0606 0.8785 0.2993
-2.750 -0.0472 0.00584 0.00129 -0.0604 0.8667 0.3413
-2.500 -0.0202 0.00570 0.00120 -0.0602 0.8545 0.3768
-2.250 0.0067 0.00558 0.00112 -0.0599 0.8417 0.4089
-2.000 0.0338 0.00547 0.00106 -0.0597 0.8286 0.4449
-1.750 0.0608 0.00536 0.00101 -0.0595 0.8153 0.4802
-1.500 0.0878 0.00527 0.00097 -0.0593 0.8017 0.5150
-1.250 0.1149 0.00520 0.00094 -0.0591 0.7877 0.5486
-1.000 0.1420 0.00514 0.00092 -0.0589 0.7734 0.5800
-0.750 0.1690 0.00510 0.00090 -0.0586 0.7586 0.6113
-0.500 0.1960 0.00506 0.00090 -0.0584 0.7432 0.6411
-0.250 0.2230 0.00505 0.00090 -0.0581 0.7276 0.6698
0.250 0.2768 0.00503 0.00093 -0.0575 0.6951 0.7256
0.500 0.3036 0.00504 0.00096 -0.0572 0.6782 0.7522
0.750 0.3302 0.00505 0.00100 -0.0568 0.6603 0.7782
1.000 0.3566 0.00509 0.00104 -0.0564 0.6420 0.8032
1.500 0.4089 0.00519 0.00114 -0.0555 0.6039 0.8492
1.750 0.4347 0.00526 0.00121 -0.0549 0.5841 0.8710
2.000 0.4598 0.00533 0.00128 -0.0542 0.5642 0.8922
2.250 0.4845 0.00542 0.00135 -0.0534 0.5425 0.9134
2.500 0.5083 0.00552 0.00142 -0.0523 0.5207 0.9348
3.000 0.5645 0.00578 0.00157 -0.0523 0.4731 0.9751
3.250 0.5999 0.00596 0.00166 -0.0540 0.4469 0.9888
3.500 0.6347 0.00617 0.00176 -0.0557 0.4184 1.0000
3.750 0.6589 0.00641 0.00189 -0.0550 0.3888 1.0000
4.000 0.6837 0.00665 0.00202 -0.0545 0.3613 1.0000
4.250 0.7089 0.00690 0.00217 -0.0541 0.3361 1.0000
4.500 0.7341 0.00717 0.00234 -0.0536 0.3079 1.0000
4.750 0.7589 0.00749 0.00253 -0.0532 0.2763 1.0000
5.000 0.7835 0.00784 0.00273 -0.0527 0.2425 1.0000
5.250 0.8079 0.00823 0.00297 -0.0522 0.2101 1.0000
5.500 0.8323 0.00861 0.00323 -0.0517 0.1794 1.0000
5.750 0.8568 0.00899 0.00349 -0.0512 0.1538 1.0000
6.000 0.8813 0.00937 0.00376 -0.0507 0.1296 1.0000
6.250 0.9054 0.00979 0.00407 -0.0502 0.1061 1.0000
6.500 0.9294 0.01022 0.00440 -0.0496 0.0862 1.0000
6.750 0.9537 0.01061 0.00473 -0.0491 0.0703 1.0000
7.000 0.9775 0.01105 0.00509 -0.0485 0.0548 1.0000
7.250 1.0005 0.01157 0.00551 -0.0479 0.0389 1.0000
7.500 1.0233 0.01210 0.00597 -0.0471 0.0265 1.0000
7.750 1.0463 0.01261 0.00648 -0.0464 0.0203 1.0000
8.000 1.0693 0.01310 0.00696 -0.0456 0.0176 1.0000
8.250 1.0916 0.01367 0.00758 -0.0447 0.0153 1.0000
8.500 1.1152 0.01406 0.00801 -0.0442 0.0143 1.0000
8.750 1.1380 0.01451 0.00849 -0.0434 0.0130 1.0000
9.000 1.1578 0.01528 0.00931 -0.0422 0.0115 1.0000
9.250 1.1786 0.01589 0.01000 -0.0412 0.0107 1.0000
9.500 1.2005 0.01637 0.01054 -0.0404 0.0100 1.0000
9.750 1.2218 0.01688 0.01109 -0.0395 0.0092 1.0000
10.000 1.2413 0.01753 0.01178 -0.0383 0.0085 1.0000
10.250 1.2519 0.01892 0.01329 -0.0359 0.0076 1.0000
10.500 1.2729 0.01934 0.01376 -0.0350 0.0073 1.0000
10.750 1.2911 0.01995 0.01444 -0.0337 0.0068 1.0000
11.000 1.3094 0.02051 0.01504 -0.0324 0.0064 1.0000
11.250 1.3258 0.02112 0.01572 -0.0309 0.0060 1.0000
11.500 1.3380 0.02184 0.01649 -0.0287 0.0057 1.0000
11.750 1.3409 0.02309 0.01783 -0.0253 0.0054 1.0000
12.000 1.3358 0.02489 0.01980 -0.0211 0.0051 1.0000
12.250 1.3471 0.02570 0.02068 -0.0192 0.0050 1.0000
12.500 1.3541 0.02684 0.02192 -0.0171 0.0049 1.0000
12.750 1.3596 0.02813 0.02331 -0.0150 0.0047 1.0000
13.000 1.3621 0.02972 0.02502 -0.0129 0.0046 1.0000
13.250 1.3631 0.03153 0.02695 -0.0111 0.0046 1.0000
13.500 1.3662 0.03330 0.02882 -0.0097 0.0044 1.0000
13.750 1.3639 0.03568 0.03133 -0.0084 0.0043 1.0000
14.000 1.3642 0.03797 0.03374 -0.0076 0.0042 1.0000
14.250 1.3631 0.04056 0.03645 -0.0072 0.0041 1.0000
14.500 1.3626 0.04327 0.03927 -0.0072 0.0040 1.0000
14.750 1.3565 0.04682 0.04294 -0.0075 0.0040 1.0000
15.000 1.3483 0.05090 0.04716 -0.0084 0.0040 1.0000
15.250 1.3424 0.05494 0.05132 -0.0097 0.0039 1.0000
15.500 1.3381 0.05899 0.05547 -0.0113 0.0038 1.0000
15.750 1.3316 0.06359 0.06018 -0.0134 0.0038 1.0000
16.000 1.3108 0.07073 0.06750 -0.0167 0.0038 1.0000
16.250 1.2985 0.07690 0.07380 -0.0200 0.0037 1.0000
16.500 1.2782 0.08474 0.08181 -0.0241 0.0038 1.0000
16.750 1.2644 0.09178 0.08897 -0.0281 0.0038 1.0000
17.000 1.2441 0.10030 0.09764 -0.0328 0.0038 1.0000
17.250 1.2261 0.10871 0.10617 -0.0377 0.0038 1.0000
17.500 1.2083 0.11730 0.11489 -0.0427 0.0037 1.0000
17.750 1.1796 0.12848 0.12626 -0.0491 0.0039 1.0000
18.000 1.1577 0.13865 0.13657 -0.0552 0.0039 1.0000
18.250 1.1401 0.14808 0.14611 -0.0608 0.0039 1.0000
18.500 1.1094 0.16126 0.15945 -0.0687 0.0040 1.0000
18.750 1.0650 0.17967 0.17807 -0.0795 0.0042 1.0000
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