E205 (10.48%) (e205-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: E205 (10.48%) (e205-il) Reynolds number: 200,000 Max Cl/Cd: 75.57 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e205-il-200000.txt Download as CSV file: xf-e205-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: E205 (10.48%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3924 0.08978 0.08639 -0.0284 1.0000 0.0536
-8.500 -0.3952 0.08605 0.08272 -0.0310 1.0000 0.0553
-8.250 -0.4049 0.08204 0.07879 -0.0355 1.0000 0.0566
-8.000 -0.3434 0.06547 0.06252 -0.0384 1.0000 0.0596
-7.750 -0.4367 0.07251 0.06920 -0.0466 1.0000 0.0577
-7.500 -0.4448 0.06632 0.06304 -0.0469 1.0000 0.0585
-7.250 -0.4354 0.06378 0.06062 -0.0444 1.0000 0.0596
-7.000 -0.4303 0.06168 0.05857 -0.0425 1.0000 0.0608
-6.750 -0.4294 0.05922 0.05612 -0.0411 1.0000 0.0620
-6.500 -0.4335 0.05683 0.05373 -0.0392 1.0000 0.0635
-6.250 -0.4197 0.04973 0.04585 -0.0472 0.9902 0.0715
-6.000 -0.3866 0.04524 0.04154 -0.0506 0.9844 0.0737
-5.750 -0.3516 0.04235 0.03852 -0.0542 0.9746 0.0803
-5.500 -0.3257 0.02903 0.02357 -0.0567 0.9611 0.0478
-5.250 -0.2912 0.02496 0.01904 -0.0581 0.9499 0.0413
-5.000 -0.2573 0.02131 0.01470 -0.0589 0.9371 0.0385
-4.750 -0.2223 0.01919 0.01220 -0.0599 0.9226 0.0381
-4.500 -0.1890 0.01766 0.01046 -0.0605 0.9059 0.0390
-4.250 -0.1581 0.01665 0.00929 -0.0607 0.8876 0.0413
-4.000 -0.1302 0.01583 0.00828 -0.0602 0.8687 0.0439
-3.750 -0.1048 0.01506 0.00735 -0.0592 0.8487 0.0454
-3.500 -0.0818 0.01400 0.00623 -0.0579 0.8306 0.0489
-3.250 -0.0575 0.01347 0.00559 -0.0569 0.8140 0.0555
-3.000 -0.0344 0.01265 0.00481 -0.0556 0.7987 0.0857
-2.750 -0.0124 0.01179 0.00441 -0.0547 0.7845 0.1967
-2.500 0.0107 0.01130 0.00422 -0.0539 0.7711 0.2940
-2.250 0.0318 0.01070 0.00411 -0.0527 0.7588 0.4352
-2.000 0.0492 0.00998 0.00407 -0.0504 0.7478 0.6233
-1.750 0.0764 0.00941 0.00413 -0.0489 0.7376 0.8350
-1.500 0.1497 0.00954 0.00416 -0.0571 0.7261 0.9518
-1.250 0.2143 0.00967 0.00404 -0.0644 0.7154 0.9882
-1.000 0.2621 0.00969 0.00382 -0.0687 0.7058 1.0000
-0.750 0.2852 0.00974 0.00373 -0.0679 0.6959 1.0000
-0.500 0.3087 0.00981 0.00368 -0.0671 0.6869 1.0000
-0.250 0.3326 0.00991 0.00362 -0.0664 0.6789 1.0000
0.000 0.3565 0.01000 0.00362 -0.0657 0.6699 1.0000
0.250 0.3808 0.01013 0.00361 -0.0649 0.6627 1.0000
0.500 0.4050 0.01023 0.00366 -0.0643 0.6542 1.0000
0.750 0.4296 0.01037 0.00368 -0.0636 0.6473 1.0000
1.000 0.4541 0.01049 0.00376 -0.0630 0.6391 1.0000
1.250 0.4789 0.01065 0.00382 -0.0624 0.6327 1.0000
1.500 0.5034 0.01078 0.00393 -0.0617 0.6248 1.0000
1.750 0.5285 0.01096 0.00401 -0.0611 0.6186 1.0000
2.000 0.5530 0.01110 0.00417 -0.0605 0.6109 1.0000
2.250 0.5783 0.01128 0.00425 -0.0599 0.6048 1.0000
2.500 0.6027 0.01143 0.00446 -0.0593 0.5971 1.0000
2.750 0.6280 0.01161 0.00457 -0.0588 0.5909 1.0000
3.000 0.6525 0.01179 0.00478 -0.0581 0.5835 1.0000
3.250 0.6777 0.01196 0.00491 -0.0576 0.5769 1.0000
3.500 0.7022 0.01214 0.00515 -0.0569 0.5693 1.0000
3.750 0.7274 0.01230 0.00527 -0.0563 0.5623 1.0000
4.000 0.7516 0.01247 0.00549 -0.0556 0.5540 1.0000
4.250 0.7769 0.01263 0.00560 -0.0550 0.5467 1.0000
4.500 0.8008 0.01277 0.00584 -0.0542 0.5375 1.0000
4.750 0.8258 0.01293 0.00598 -0.0536 0.5298 1.0000
5.000 0.8498 0.01305 0.00616 -0.0528 0.5202 1.0000
5.250 0.8739 0.01319 0.00635 -0.0520 0.5110 1.0000
5.500 0.8988 0.01331 0.00646 -0.0513 0.5022 1.0000
5.750 0.9221 0.01341 0.00667 -0.0504 0.4911 1.0000
6.000 0.9457 0.01352 0.00685 -0.0495 0.4800 1.0000
6.250 0.9693 0.01363 0.00703 -0.0486 0.4685 1.0000
6.500 0.9927 0.01373 0.00718 -0.0477 0.4561 1.0000
6.750 1.0154 0.01383 0.00735 -0.0467 0.4416 1.0000
7.000 1.0376 0.01394 0.00754 -0.0456 0.4249 1.0000
7.250 1.0595 0.01409 0.00777 -0.0444 0.4065 1.0000
7.500 1.0806 0.01430 0.00801 -0.0432 0.3854 1.0000
7.750 1.1002 0.01457 0.00829 -0.0417 0.3562 1.0000
8.000 1.1169 0.01504 0.00866 -0.0399 0.3144 1.0000
8.500 1.1385 0.01705 0.01011 -0.0351 0.2046 1.0000
8.750 1.1474 0.01828 0.01108 -0.0327 0.1602 1.0000
9.000 1.1567 0.01945 0.01207 -0.0303 0.1263 1.0000
9.250 1.1654 0.02061 0.01311 -0.0278 0.0999 1.0000
9.500 1.1707 0.02192 0.01429 -0.0250 0.0742 1.0000
9.750 1.1667 0.02356 0.01577 -0.0208 0.0513 1.0000
10.000 1.1549 0.02572 0.01783 -0.0161 0.0377 1.0000
10.250 1.1556 0.02733 0.01952 -0.0133 0.0319 1.0000
10.500 1.1474 0.02971 0.02193 -0.0106 0.0291 1.0000
10.750 1.1524 0.03134 0.02369 -0.0090 0.0269 1.0000
11.000 1.1543 0.03334 0.02579 -0.0077 0.0247 1.0000
11.250 1.1556 0.03550 0.02803 -0.0065 0.0238 1.0000
11.500 1.1540 0.03807 0.03064 -0.0053 0.0226 1.0000
11.750 1.1544 0.04062 0.03324 -0.0039 0.0220 1.0000
12.000 1.1610 0.04269 0.03540 -0.0027 0.0214 1.0000
12.250 1.1687 0.04473 0.03759 -0.0017 0.0207 1.0000
12.500 1.1775 0.04681 0.03981 -0.0006 0.0202 1.0000
12.750 1.1860 0.04905 0.04219 0.0004 0.0198 1.0000
13.000 1.1935 0.05151 0.04483 0.0013 0.0196 1.0000
13.250 1.1985 0.05432 0.04785 0.0021 0.0193 1.0000
13.500 1.2005 0.05743 0.05117 0.0025 0.0193 1.0000
13.750 1.1986 0.06106 0.05507 0.0027 0.0193 1.0000
14.000 1.1939 0.06468 0.05890 0.0023 0.0189 1.0000
14.250 1.1860 0.06899 0.06345 0.0017 0.0189 1.0000
14.500 1.1765 0.07342 0.06809 0.0006 0.0187 1.0000
14.750 1.1613 0.07898 0.07391 -0.0010 0.0190 1.0000
15.000 1.1523 0.08344 0.07852 -0.0029 0.0184 1.0000
15.250 1.1342 0.08982 0.08514 -0.0057 0.0186 1.0000
15.500 1.1201 0.09576 0.09125 -0.0086 0.0184 1.0000
15.750 1.0893 0.10552 0.10131 -0.0138 0.0194 1.0000
16.000 1.0700 0.11340 0.10938 -0.0185 0.0193 1.0000
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Polar data table (+)
Polar graphs
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