E209 (13.72%) (e209-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: E209 (13.72%) (e209-il) Reynolds number: 500,000 Max Cl/Cd: 93.02 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e209-il-500000-n5.txt Download as CSV file: xf-e209-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: E209 (13.72%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.000 -0.7798 0.09926 0.09624 -0.0346 1.0000 0.0058
-15.750 -0.8068 0.08978 0.08665 -0.0398 1.0000 0.0059
-15.500 -0.8290 0.08155 0.07827 -0.0443 1.0000 0.0058
-15.250 -0.8504 0.07379 0.07038 -0.0487 1.0000 0.0058
-15.000 -0.8709 0.06674 0.06318 -0.0527 1.0000 0.0058
-14.750 -0.8855 0.06102 0.05732 -0.0559 1.0000 0.0058
-14.500 -0.9001 0.05556 0.05172 -0.0588 1.0000 0.0057
-14.250 -0.9125 0.05066 0.04669 -0.0614 1.0000 0.0058
-14.000 -0.9202 0.04660 0.04251 -0.0633 1.0000 0.0058
-13.750 -0.9292 0.04254 0.03832 -0.0652 1.0000 0.0059
-13.500 -0.9341 0.03918 0.03483 -0.0664 1.0000 0.0059
-13.250 -0.9353 0.03643 0.03198 -0.0673 1.0000 0.0061
-13.000 -0.9356 0.03400 0.02945 -0.0676 1.0000 0.0062
-12.750 -0.9376 0.03170 0.02702 -0.0674 1.0000 0.0062
-12.500 -0.9370 0.02994 0.02518 -0.0665 1.0000 0.0064
-12.250 -0.9399 0.02827 0.02339 -0.0647 1.0000 0.0065
-12.000 -0.9389 0.02722 0.02226 -0.0622 1.0000 0.0066
-11.750 -0.9445 0.02616 0.02112 -0.0582 1.0000 0.0067
-11.500 -0.9400 0.02549 0.02039 -0.0551 1.0000 0.0070
-11.250 -0.9383 0.02435 0.01913 -0.0518 1.0000 0.0070
-11.000 -0.9308 0.02352 0.01822 -0.0491 1.0000 0.0073
-10.750 -0.9210 0.02278 0.01740 -0.0467 1.0000 0.0076
-10.500 -0.9037 0.02192 0.01641 -0.0457 0.9990 0.0078
-10.250 -0.8755 0.02086 0.01524 -0.0470 0.9958 0.0082
-10.000 -0.8478 0.01986 0.01417 -0.0482 0.9924 0.0086
-9.750 -0.8189 0.01917 0.01343 -0.0492 0.9886 0.0092
-9.500 -0.7885 0.01839 0.01257 -0.0506 0.9850 0.0097
-9.250 -0.7586 0.01766 0.01176 -0.0517 0.9812 0.0103
-9.000 -0.7313 0.01700 0.01100 -0.0522 0.9752 0.0108
-8.500 -0.6751 0.01568 0.00958 -0.0534 0.9618 0.0125
-8.250 -0.6449 0.01516 0.00901 -0.0543 0.9539 0.0136
-8.000 -0.6146 0.01468 0.00846 -0.0551 0.9427 0.0147
-7.750 -0.5834 0.01404 0.00775 -0.0562 0.9285 0.0160
-7.500 -0.5498 0.01351 0.00715 -0.0577 0.9098 0.0174
-7.250 -0.5186 0.01310 0.00661 -0.0586 0.8847 0.0189
-7.000 -0.4926 0.01275 0.00612 -0.0583 0.8567 0.0204
-6.750 -0.4687 0.01244 0.00569 -0.0576 0.8302 0.0226
-6.500 -0.4447 0.01221 0.00531 -0.0569 0.8060 0.0249
-6.250 -0.4210 0.01193 0.00494 -0.0562 0.7840 0.0288
-6.000 -0.3969 0.01168 0.00460 -0.0555 0.7644 0.0344
-5.750 -0.3728 0.01140 0.00429 -0.0549 0.7463 0.0451
-5.500 -0.3483 0.01112 0.00399 -0.0543 0.7300 0.0591
-5.250 -0.3235 0.01088 0.00372 -0.0539 0.7151 0.0737
-5.000 -0.2983 0.01066 0.00348 -0.0534 0.7012 0.0899
-4.500 -0.2477 0.01017 0.00302 -0.0527 0.6761 0.1335
-4.250 -0.2227 0.00986 0.00280 -0.0523 0.6650 0.1693
-4.000 -0.1977 0.00954 0.00259 -0.0520 0.6547 0.2111
-3.750 -0.1725 0.00924 0.00240 -0.0516 0.6448 0.2539
-3.500 -0.1475 0.00889 0.00222 -0.0513 0.6358 0.3102
-3.250 -0.1221 0.00865 0.00211 -0.0510 0.6271 0.3631
-3.000 -0.0952 0.00854 0.00204 -0.0508 0.6187 0.3927
-2.750 -0.0683 0.00847 0.00198 -0.0506 0.6112 0.4188
-2.500 -0.0409 0.00843 0.00193 -0.0505 0.6033 0.4407
-2.250 -0.0135 0.00841 0.00188 -0.0504 0.5963 0.4548
-2.000 0.0141 0.00838 0.00184 -0.0503 0.5892 0.4667
-1.750 0.0415 0.00838 0.00180 -0.0502 0.5826 0.4776
-1.500 0.0694 0.00836 0.00177 -0.0501 0.5759 0.4884
-1.250 0.0969 0.00836 0.00174 -0.0500 0.5696 0.4993
-1.000 0.1246 0.00834 0.00173 -0.0500 0.5636 0.5094
-0.750 0.1523 0.00835 0.00171 -0.0499 0.5572 0.5188
-0.500 0.1799 0.00836 0.00171 -0.0498 0.5517 0.5290
-0.250 0.2077 0.00834 0.00171 -0.0498 0.5457 0.5390
0.000 0.2353 0.00836 0.00171 -0.0497 0.5398 0.5489
0.250 0.2629 0.00836 0.00173 -0.0497 0.5344 0.5593
0.500 0.2906 0.00836 0.00175 -0.0496 0.5288 0.5693
1.000 0.3458 0.00839 0.00180 -0.0495 0.5177 0.5894
1.250 0.3733 0.00841 0.00184 -0.0494 0.5122 0.5996
1.500 0.4007 0.00844 0.00188 -0.0493 0.5069 0.6108
1.750 0.4283 0.00845 0.00194 -0.0493 0.5013 0.6234
2.000 0.4556 0.00847 0.00200 -0.0491 0.4959 0.6368
2.250 0.4828 0.00849 0.00206 -0.0490 0.4907 0.6508
2.500 0.5100 0.00851 0.00214 -0.0489 0.4847 0.6671
2.750 0.5367 0.00854 0.00222 -0.0486 0.4792 0.6851
3.000 0.5636 0.00854 0.00231 -0.0485 0.4729 0.7049
3.250 0.5900 0.00857 0.00240 -0.0481 0.4657 0.7263
3.500 0.6163 0.00858 0.00251 -0.0478 0.4579 0.7501
3.750 0.6417 0.00861 0.00261 -0.0473 0.4497 0.7783
4.000 0.6672 0.00861 0.00274 -0.0467 0.4416 0.8102
4.250 0.6915 0.00863 0.00287 -0.0459 0.4334 0.8460
4.500 0.7162 0.00865 0.00300 -0.0451 0.4242 0.8857
4.750 0.7458 0.00873 0.00317 -0.0454 0.4142 0.9288
5.000 0.7823 0.00889 0.00333 -0.0473 0.4018 0.9606
5.250 0.8173 0.00906 0.00349 -0.0490 0.3892 0.9805
5.500 0.8520 0.00926 0.00366 -0.0506 0.3742 0.9933
5.750 0.8818 0.00948 0.00385 -0.0513 0.3577 1.0000
6.000 0.9039 0.00972 0.00405 -0.0503 0.3393 1.0000
6.250 0.9253 0.01003 0.00427 -0.0492 0.3185 1.0000
6.500 0.9471 0.01033 0.00452 -0.0482 0.2977 1.0000
6.750 0.9673 0.01076 0.00484 -0.0469 0.2690 1.0000
7.000 0.9858 0.01132 0.00523 -0.0455 0.2343 1.0000
7.250 1.0035 0.01193 0.00567 -0.0439 0.2010 1.0000
7.500 1.0207 0.01258 0.00616 -0.0423 0.1681 1.0000
7.750 1.0382 0.01320 0.00664 -0.0408 0.1416 1.0000
8.000 1.0560 0.01378 0.00713 -0.0393 0.1209 1.0000
8.250 1.0743 0.01430 0.00760 -0.0379 0.1052 1.0000
8.500 1.0922 0.01483 0.00808 -0.0364 0.0913 1.0000
8.750 1.1091 0.01539 0.00859 -0.0348 0.0782 1.0000
9.000 1.1253 0.01596 0.00912 -0.0331 0.0675 1.0000
9.250 1.1396 0.01656 0.00969 -0.0312 0.0571 1.0000
9.500 1.1513 0.01717 0.01027 -0.0287 0.0479 1.0000
9.750 1.1636 0.01774 0.01084 -0.0264 0.0417 1.0000
10.000 1.1739 0.01844 0.01152 -0.0239 0.0348 1.0000
10.250 1.1847 0.01913 0.01222 -0.0216 0.0302 1.0000
10.500 1.1960 0.01984 0.01295 -0.0195 0.0268 1.0000
10.750 1.2056 0.02066 0.01380 -0.0174 0.0235 1.0000
11.000 1.2154 0.02151 0.01470 -0.0154 0.0211 1.0000
11.250 1.2244 0.02245 0.01568 -0.0135 0.0190 1.0000
11.500 1.2313 0.02359 0.01684 -0.0116 0.0168 1.0000
11.750 1.2400 0.02469 0.01800 -0.0101 0.0153 1.0000
12.000 1.2471 0.02597 0.01934 -0.0086 0.0140 1.0000
12.250 1.2526 0.02746 0.02088 -0.0073 0.0128 1.0000
12.500 1.2597 0.02892 0.02242 -0.0062 0.0118 1.0000
12.750 1.2657 0.03053 0.02410 -0.0053 0.0109 1.0000
13.000 1.2699 0.03240 0.02604 -0.0045 0.0101 1.0000
13.250 1.2733 0.03442 0.02813 -0.0039 0.0093 1.0000
13.500 1.2776 0.03643 0.03023 -0.0034 0.0090 1.0000
13.750 1.2817 0.03852 0.03241 -0.0030 0.0084 1.0000
14.000 1.2839 0.04085 0.03482 -0.0028 0.0079 1.0000
14.250 1.2852 0.04333 0.03737 -0.0026 0.0074 1.0000
14.500 1.2833 0.04624 0.04036 -0.0026 0.0069 1.0000
14.750 1.2839 0.04893 0.04314 -0.0028 0.0069 1.0000
15.000 1.2835 0.05183 0.04615 -0.0030 0.0065 1.0000
15.250 1.2835 0.05475 0.04917 -0.0034 0.0063 1.0000
15.500 1.2828 0.05785 0.05236 -0.0039 0.0060 1.0000
15.750 1.2824 0.06098 0.05558 -0.0046 0.0057 1.0000
16.000 1.2792 0.06460 0.05930 -0.0054 0.0054 1.0000
16.250 1.2766 0.06820 0.06300 -0.0064 0.0053 1.0000
16.500 1.2712 0.07233 0.06724 -0.0077 0.0053 1.0000
16.750 1.2674 0.07632 0.07131 -0.0090 0.0050 1.0000
17.000 1.2583 0.08123 0.07633 -0.0108 0.0048 1.0000
17.250 1.2546 0.08542 0.08063 -0.0123 0.0048 1.0000
17.500 1.2488 0.09006 0.08539 -0.0142 0.0047 1.0000
17.750 1.2417 0.09502 0.09046 -0.0163 0.0046 1.0000
18.000 1.2350 0.09998 0.09555 -0.0184 0.0045 1.0000
18.250 1.2259 0.10551 0.10119 -0.0210 0.0045 1.0000
18.500 1.2187 0.11078 0.10658 -0.0235 0.0044 1.0000
18.750 1.2102 0.11640 0.11231 -0.0262 0.0043 1.0000
19.000 1.2009 0.12225 0.11829 -0.0292 0.0043 1.0000
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Polar data table (+)
Polar graphs
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