E203 (13.64%) (e203-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: E203 (13.64%) (e203-il) Reynolds number: 50,000 Max Cl/Cd: 31.22 at α=8.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e203-il-50000-n5.txt Download as CSV file: xf-e203-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: E203 (13.64%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.4365 0.10399 0.09666 -0.0477 1.0000 0.0542
-11.000 -0.4441 0.09830 0.09105 -0.0500 1.0000 0.0538
-10.750 -0.4553 0.09179 0.08462 -0.0529 1.0000 0.0533
-10.500 -0.4726 0.08438 0.07729 -0.0567 1.0000 0.0527
-10.250 -0.4987 0.07648 0.06943 -0.0614 1.0000 0.0519
-10.000 -0.5300 0.06952 0.06247 -0.0655 1.0000 0.0510
-9.750 -0.5620 0.06450 0.05742 -0.0672 1.0000 0.0504
-9.500 -0.5913 0.06098 0.05386 -0.0660 1.0000 0.0500
-9.250 -0.6116 0.05758 0.05031 -0.0644 1.0000 0.0499
-9.000 -0.6258 0.05442 0.04697 -0.0625 1.0000 0.0500
-8.750 -0.6344 0.05148 0.04381 -0.0604 1.0000 0.0503
-8.500 -0.6385 0.04872 0.04080 -0.0582 1.0000 0.0507
-8.250 -0.6389 0.04613 0.03794 -0.0561 1.0000 0.0514
-8.000 -0.6360 0.04375 0.03528 -0.0539 1.0000 0.0523
-7.750 -0.6304 0.04154 0.03278 -0.0518 1.0000 0.0534
-7.500 -0.6224 0.03956 0.03050 -0.0497 1.0000 0.0548
-7.250 -0.6131 0.03787 0.02840 -0.0476 1.0000 0.0571
-7.000 -0.6034 0.03647 0.02710 -0.0458 1.0000 0.0598
-6.750 -0.5814 0.03504 0.02553 -0.0460 0.9962 0.0642
-6.500 -0.5470 0.03332 0.02339 -0.0477 0.9883 0.0696
-6.250 -0.5151 0.03176 0.02188 -0.0495 0.9799 0.0761
-6.000 -0.4827 0.03029 0.02034 -0.0515 0.9711 0.0900
-5.750 -0.4537 0.02883 0.01889 -0.0531 0.9609 0.1118
-5.500 -0.4244 0.02736 0.01757 -0.0550 0.9513 0.1527
-5.250 -0.3930 0.02588 0.01648 -0.0574 0.9427 0.2164
-5.000 -0.3661 0.02490 0.01582 -0.0584 0.9321 0.2846
-4.750 -0.3369 0.02455 0.01573 -0.0590 0.9224 0.3558
-4.500 -0.3022 0.02457 0.01569 -0.0603 0.9144 0.4171
-4.250 -0.2747 0.02464 0.01563 -0.0602 0.9039 0.4579
-4.000 -0.2431 0.02470 0.01553 -0.0607 0.8955 0.4926
-3.750 -0.2111 0.02471 0.01539 -0.0612 0.8873 0.5221
-3.500 -0.1826 0.02474 0.01529 -0.0611 0.8784 0.5461
-3.250 -0.1486 0.02466 0.01506 -0.0619 0.8716 0.5698
-3.000 -0.1223 0.02464 0.01493 -0.0614 0.8622 0.5892
-2.750 -0.0882 0.02451 0.01464 -0.0623 0.8560 0.6097
-2.500 -0.0633 0.02447 0.01447 -0.0618 0.8464 0.6269
-2.250 -0.0290 0.02432 0.01420 -0.0627 0.8406 0.6437
-2.000 -0.0057 0.02432 0.01411 -0.0619 0.8309 0.6589
-1.750 0.0286 0.02415 0.01382 -0.0628 0.8255 0.6748
-1.500 0.0509 0.02418 0.01379 -0.0619 0.8156 0.6895
-1.250 0.0836 0.02405 0.01356 -0.0625 0.8099 0.7047
-1.000 0.1062 0.02410 0.01357 -0.0617 0.8007 0.7194
-0.750 0.1385 0.02397 0.01337 -0.0623 0.7951 0.7347
-0.500 0.1599 0.02407 0.01346 -0.0613 0.7860 0.7501
-0.250 0.1926 0.02393 0.01328 -0.0619 0.7810 0.7668
0.000 0.2120 0.02410 0.01347 -0.0606 0.7715 0.7844
0.250 0.2441 0.02399 0.01334 -0.0611 0.7665 0.8047
0.500 0.2638 0.02419 0.01360 -0.0598 0.7575 0.8267
0.750 0.2975 0.02410 0.01352 -0.0606 0.7522 0.8525
1.000 0.3252 0.02433 0.01381 -0.0609 0.7440 0.8831
1.250 0.3715 0.02430 0.01379 -0.0644 0.7386 0.9172
1.500 0.4188 0.02447 0.01397 -0.0688 0.7315 0.9609
1.750 0.4583 0.02463 0.01408 -0.0720 0.7248 1.0000
2.000 0.4780 0.02500 0.01436 -0.0714 0.7173 1.0000
2.250 0.5009 0.02536 0.01466 -0.0712 0.7101 1.0000
2.500 0.5246 0.02576 0.01502 -0.0710 0.7032 1.0000
2.750 0.5469 0.02622 0.01545 -0.0706 0.6956 1.0000
3.000 0.5730 0.02659 0.01579 -0.0706 0.6893 1.0000
3.250 0.5929 0.02717 0.01638 -0.0698 0.6811 1.0000
3.500 0.6216 0.02746 0.01670 -0.0701 0.6754 1.0000
3.750 0.6388 0.02818 0.01745 -0.0689 0.6664 1.0000
4.000 0.6681 0.02844 0.01775 -0.0691 0.6606 1.0000
4.250 0.6845 0.02921 0.01858 -0.0679 0.6514 1.0000
4.500 0.7101 0.02961 0.01907 -0.0676 0.6444 1.0000
4.750 0.7310 0.03018 0.01972 -0.0668 0.6357 1.0000
5.000 0.7505 0.03082 0.02044 -0.0658 0.6268 1.0000
5.250 0.7796 0.03098 0.02070 -0.0657 0.6194 1.0000
5.500 0.7946 0.03177 0.02163 -0.0641 0.6087 1.0000
5.750 0.8275 0.03169 0.02165 -0.0643 0.6015 1.0000
6.000 0.8452 0.03227 0.02237 -0.0629 0.5904 1.0000
6.250 0.8616 0.03290 0.02312 -0.0613 0.5790 1.0000
6.500 0.8860 0.03306 0.02346 -0.0604 0.5685 1.0000
6.750 0.9206 0.03260 0.02316 -0.0603 0.5587 1.0000
7.000 0.9378 0.03296 0.02367 -0.0585 0.5452 1.0000
7.250 0.9571 0.03312 0.02399 -0.0568 0.5312 1.0000
7.500 0.9779 0.03310 0.02417 -0.0552 0.5165 1.0000
7.750 1.0001 0.03290 0.02413 -0.0535 0.5007 1.0000
8.000 1.0144 0.03307 0.02446 -0.0511 0.4830 1.0000
8.250 1.0234 0.03347 0.02501 -0.0482 0.4636 1.0000
8.500 1.0396 0.03330 0.02495 -0.0457 0.4427 1.0000
8.750 1.0438 0.03393 0.02570 -0.0424 0.4196 1.0000
9.000 1.0529 0.03431 0.02618 -0.0396 0.3933 1.0000
9.250 1.0598 0.03495 0.02684 -0.0368 0.3632 1.0000
9.500 1.0655 0.03580 0.02763 -0.0342 0.3303 1.0000
9.750 1.0690 0.03699 0.02863 -0.0316 0.2963 1.0000
10.000 1.0682 0.03876 0.03024 -0.0293 0.2640 1.0000
10.250 1.0661 0.04088 0.03218 -0.0273 0.2355 1.0000
10.500 1.0628 0.04329 0.03441 -0.0256 0.2105 1.0000
10.750 1.0599 0.04589 0.03693 -0.0243 0.1876 1.0000
11.000 1.0570 0.04859 0.03950 -0.0232 0.1690 1.0000
11.250 1.0552 0.05138 0.04224 -0.0223 0.1507 1.0000
11.500 1.0540 0.05420 0.04506 -0.0215 0.1350 1.0000
11.750 1.0530 0.05710 0.04794 -0.0209 0.1208 1.0000
12.000 1.0525 0.06005 0.05086 -0.0205 0.1083 1.0000
12.250 1.0519 0.06307 0.05387 -0.0202 0.0971 1.0000
12.500 1.0508 0.06619 0.05691 -0.0200 0.0874 1.0000
12.750 1.0507 0.06941 0.06026 -0.0200 0.0777 1.0000
13.000 1.0516 0.07262 0.06358 -0.0200 0.0697 1.0000
13.250 1.0507 0.07591 0.06682 -0.0203 0.0636 1.0000
13.500 1.0536 0.07922 0.07038 -0.0203 0.0577 1.0000
13.750 1.0540 0.08258 0.07376 -0.0207 0.0533 1.0000
14.000 1.0568 0.08601 0.07737 -0.0208 0.0496 1.0000
14.250 1.0577 0.08990 0.08154 -0.0213 0.0467 1.0000
14.500 1.0571 0.09388 0.08573 -0.0221 0.0445 1.0000
14.750 1.0577 0.09746 0.08934 -0.0230 0.0423 1.0000
15.000 1.0535 0.10225 0.09430 -0.0245 0.0409 1.0000
15.250 1.0430 0.10840 0.10078 -0.0271 0.0401 1.0000
15.500 1.0291 0.11544 0.10811 -0.0305 0.0395 1.0000
15.750 1.0137 0.12315 0.11606 -0.0346 0.0394 1.0000
16.000 0.9948 0.13217 0.12531 -0.0398 0.0394 1.0000
16.250 0.9734 0.14262 0.13590 -0.0461 0.0398 1.0000
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Polar data table (+)
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