E224 (10.17%) (e224-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: E224 (10.17%) (e224-il) Reynolds number: 1,000,000 Max Cl/Cd: 88.89 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e224-il-1000000-n5.txt Download as CSV file: xf-e224-il-1000000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.250 -0.7474 0.08300 0.08113 -0.0307 1.0000 0.0029
-13.000 -0.7868 0.07088 0.06892 -0.0373 1.0000 0.0028
-12.750 -0.8526 0.05220 0.04998 -0.0504 1.0000 0.0027
-12.500 -0.8754 0.04311 0.04069 -0.0587 1.0000 0.0026
-12.250 -0.8883 0.03782 0.03524 -0.0631 1.0000 0.0027
-12.000 -0.8972 0.03468 0.03197 -0.0641 1.0000 0.0027
-11.750 -0.9195 0.03194 0.02905 -0.0612 1.0000 0.0027
-11.500 -0.9215 0.03011 0.02707 -0.0589 1.0000 0.0028
-11.250 -0.9212 0.02817 0.02496 -0.0567 1.0000 0.0028
-11.000 -0.9190 0.02622 0.02281 -0.0543 1.0000 0.0028
-10.750 -0.9099 0.02489 0.02133 -0.0524 1.0000 0.0028
-10.500 -0.9004 0.02352 0.01980 -0.0503 1.0000 0.0029
-10.250 -0.8843 0.02218 0.01830 -0.0494 0.9995 0.0029
-10.000 -0.8580 0.02078 0.01671 -0.0505 0.9977 0.0030
-9.750 -0.8311 0.01941 0.01515 -0.0516 0.9957 0.0030
-9.500 -0.8024 0.01834 0.01394 -0.0527 0.9941 0.0031
-9.250 -0.7757 0.01751 0.01300 -0.0532 0.9916 0.0032
-9.000 -0.7482 0.01648 0.01184 -0.0539 0.9890 0.0032
-8.750 -0.7185 0.01578 0.01104 -0.0549 0.9867 0.0033
-8.500 -0.6885 0.01488 0.01002 -0.0560 0.9847 0.0033
-8.250 -0.6584 0.01369 0.00865 -0.0572 0.9830 0.0035
-8.000 -0.6327 0.01304 0.00794 -0.0572 0.9783 0.0038
-7.750 -0.6036 0.01249 0.00733 -0.0578 0.9745 0.0041
-7.500 -0.5729 0.01198 0.00675 -0.0586 0.9713 0.0043
-7.250 -0.5441 0.01150 0.00621 -0.0591 0.9667 0.0046
-7.000 -0.5154 0.01104 0.00569 -0.0594 0.9609 0.0048
-6.750 -0.4843 0.01063 0.00520 -0.0603 0.9560 0.0051
-6.500 -0.4562 0.01026 0.00478 -0.0604 0.9477 0.0053
-6.250 -0.4269 0.00994 0.00439 -0.0608 0.9396 0.0056
-6.000 -0.3991 0.00956 0.00393 -0.0608 0.9297 0.0062
-5.750 -0.3719 0.00926 0.00359 -0.0607 0.9193 0.0072
-5.500 -0.3448 0.00901 0.00328 -0.0606 0.9088 0.0083
-5.250 -0.3181 0.00876 0.00300 -0.0603 0.8977 0.0118
-5.000 -0.2915 0.00853 0.00275 -0.0601 0.8860 0.0170
-4.750 -0.2649 0.00832 0.00252 -0.0598 0.8739 0.0230
-4.500 -0.2382 0.00812 0.00231 -0.0596 0.8615 0.0316
-4.250 -0.2117 0.00791 0.00210 -0.0594 0.8485 0.0450
-4.000 -0.1851 0.00771 0.00192 -0.0591 0.8352 0.0628
-3.750 -0.1588 0.00745 0.00173 -0.0589 0.8220 0.0915
-3.500 -0.1322 0.00724 0.00158 -0.0587 0.8089 0.1204
-3.250 -0.1053 0.00709 0.00144 -0.0585 0.7955 0.1435
-3.000 -0.0787 0.00688 0.00132 -0.0583 0.7821 0.1806
-2.750 -0.0520 0.00669 0.00121 -0.0582 0.7684 0.2196
-2.500 -0.0249 0.00658 0.00112 -0.0580 0.7538 0.2449
-2.250 0.0022 0.00649 0.00104 -0.0579 0.7391 0.2693
-2.000 0.0292 0.00639 0.00097 -0.0577 0.7240 0.3002
-1.750 0.0563 0.00630 0.00092 -0.0576 0.7086 0.3308
-1.500 0.0835 0.00622 0.00087 -0.0575 0.6931 0.3610
-1.250 0.1106 0.00616 0.00083 -0.0573 0.6773 0.3913
-1.000 0.1378 0.00611 0.00081 -0.0572 0.6608 0.4195
-0.750 0.1649 0.00608 0.00080 -0.0571 0.6441 0.4478
-0.500 0.1921 0.00606 0.00079 -0.0569 0.6267 0.4756
-0.250 0.2193 0.00605 0.00079 -0.0568 0.6088 0.5030
0.000 0.2465 0.00604 0.00080 -0.0567 0.5911 0.5301
0.250 0.2736 0.00606 0.00082 -0.0565 0.5727 0.5572
0.500 0.3007 0.00607 0.00085 -0.0564 0.5547 0.5851
0.750 0.3278 0.00608 0.00089 -0.0562 0.5352 0.6142
1.250 0.3816 0.00618 0.00099 -0.0558 0.4948 0.6679
1.500 0.4084 0.00624 0.00105 -0.0556 0.4746 0.6926
1.750 0.4352 0.00631 0.00113 -0.0554 0.4539 0.7164
2.000 0.4618 0.00641 0.00121 -0.0551 0.4316 0.7412
2.250 0.4882 0.00650 0.00131 -0.0549 0.4103 0.7660
2.500 0.5143 0.00662 0.00141 -0.0545 0.3868 0.7904
2.750 0.5403 0.00674 0.00153 -0.0541 0.3630 0.8141
3.000 0.5661 0.00687 0.00165 -0.0537 0.3426 0.8369
3.250 0.5914 0.00702 0.00178 -0.0532 0.3188 0.8594
3.500 0.6163 0.00717 0.00192 -0.0525 0.2965 0.8818
3.750 0.6403 0.00737 0.00208 -0.0517 0.2700 0.9039
4.000 0.6635 0.00762 0.00224 -0.0507 0.2385 0.9272
4.250 0.6881 0.00781 0.00240 -0.0500 0.2180 0.9523
4.500 0.7188 0.00812 0.00259 -0.0508 0.1877 0.9779
4.750 0.7502 0.00844 0.00281 -0.0518 0.1616 1.0000
5.000 0.7753 0.00875 0.00303 -0.0515 0.1392 1.0000
5.250 0.8001 0.00911 0.00327 -0.0510 0.1155 1.0000
5.500 0.8250 0.00945 0.00352 -0.0506 0.0971 1.0000
5.750 0.8500 0.00979 0.00378 -0.0502 0.0813 1.0000
6.000 0.8749 0.01013 0.00406 -0.0497 0.0666 1.0000
6.250 0.8997 0.01048 0.00435 -0.0493 0.0540 1.0000
6.500 0.9245 0.01082 0.00465 -0.0489 0.0443 1.0000
6.750 0.9490 0.01118 0.00497 -0.0484 0.0355 1.0000
7.000 0.9733 0.01157 0.00532 -0.0479 0.0271 1.0000
7.250 0.9974 0.01197 0.00570 -0.0474 0.0208 1.0000
7.500 1.0217 0.01234 0.00607 -0.0468 0.0170 1.0000
7.750 1.0453 0.01276 0.00648 -0.0462 0.0142 1.0000
8.000 1.0694 0.01313 0.00687 -0.0457 0.0126 1.0000
8.250 1.0935 0.01348 0.00726 -0.0452 0.0118 1.0000
8.500 1.1170 0.01388 0.00767 -0.0446 0.0108 1.0000
8.750 1.1399 0.01432 0.00815 -0.0439 0.0099 1.0000
9.000 1.1621 0.01483 0.00870 -0.0431 0.0089 1.0000
9.250 1.1852 0.01521 0.00912 -0.0424 0.0086 1.0000
9.500 1.2079 0.01562 0.00958 -0.0417 0.0081 1.0000
9.750 1.2301 0.01604 0.01004 -0.0410 0.0074 1.0000
10.000 1.2515 0.01653 0.01056 -0.0402 0.0066 1.0000
10.250 1.2717 0.01710 0.01117 -0.0391 0.0057 1.0000
10.500 1.2927 0.01757 0.01168 -0.0382 0.0052 1.0000
10.750 1.3125 0.01811 0.01226 -0.0372 0.0046 1.0000
11.000 1.3313 0.01870 0.01288 -0.0360 0.0040 1.0000
11.250 1.3485 0.01938 0.01361 -0.0346 0.0036 1.0000
11.500 1.3655 0.02003 0.01433 -0.0331 0.0034 1.0000
11.750 1.3804 0.02068 0.01505 -0.0313 0.0032 1.0000
12.000 1.3929 0.02136 0.01580 -0.0292 0.0030 1.0000
12.250 1.4039 0.02211 0.01662 -0.0268 0.0028 1.0000
12.500 1.4141 0.02293 0.01752 -0.0245 0.0026 1.0000
12.750 1.4234 0.02381 0.01847 -0.0223 0.0025 1.0000
13.000 1.4310 0.02484 0.01958 -0.0200 0.0024 1.0000
13.250 1.4367 0.02604 0.02087 -0.0177 0.0022 1.0000
13.500 1.4417 0.02734 0.02228 -0.0156 0.0021 1.0000
13.750 1.4436 0.02894 0.02399 -0.0134 0.0020 1.0000
14.000 1.4457 0.03063 0.02580 -0.0116 0.0020 1.0000
14.250 1.4494 0.03229 0.02755 -0.0102 0.0020 1.0000
14.500 1.4500 0.03433 0.02971 -0.0090 0.0020 1.0000
14.750 1.4541 0.03617 0.03165 -0.0082 0.0019 1.0000
15.000 1.4503 0.03892 0.03453 -0.0075 0.0019 1.0000
15.250 1.4494 0.04154 0.03727 -0.0073 0.0019 1.0000
15.500 1.4483 0.04438 0.04021 -0.0073 0.0018 1.0000
15.750 1.4391 0.04838 0.04436 -0.0080 0.0018 1.0000
16.000 1.4322 0.05236 0.04849 -0.0090 0.0018 1.0000
16.250 1.4242 0.05674 0.05300 -0.0105 0.0018 1.0000
16.500 1.4151 0.06155 0.05794 -0.0125 0.0017 1.0000
16.750 1.4002 0.06758 0.06412 -0.0153 0.0017 1.0000
17.000 1.3830 0.07436 0.07105 -0.0187 0.0017 1.0000
17.250 1.3670 0.08127 0.07810 -0.0223 0.0017 1.0000
17.500 1.3464 0.08933 0.08631 -0.0268 0.0017 1.0000
17.750 1.3168 0.09960 0.09676 -0.0326 0.0017 1.0000
18.000 1.2926 0.10908 0.10639 -0.0380 0.0017 1.0000
18.250 1.2611 0.12052 0.11797 -0.0446 0.0018 1.0000
18.500 1.2332 0.13145 0.12904 -0.0510 0.0018 1.0000
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Polar data table (+)
Polar graphs
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