E209 (13.72%) (e209-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: E209 (13.72%) (e209-il) Reynolds number: 1,000,000 Max Cl/Cd: 121.64 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e209-il-1000000.txt Download as CSV file: xf-e209-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.000 -0.7738 0.10041 0.09824 -0.0336 1.0000 0.0069
-15.750 -0.8197 0.08706 0.08470 -0.0410 1.0000 0.0068
-15.500 -0.8391 0.07927 0.07679 -0.0456 1.0000 0.0068
-15.250 -0.8546 0.07257 0.06998 -0.0496 1.0000 0.0068
-15.000 -0.8771 0.06521 0.06248 -0.0539 1.0000 0.0068
-14.750 -0.9020 0.05805 0.05515 -0.0579 1.0000 0.0067
-14.500 -0.9205 0.05218 0.04912 -0.0611 1.0000 0.0067
-14.250 -0.9234 0.04858 0.04543 -0.0632 1.0000 0.0068
-14.000 -0.9390 0.04355 0.04024 -0.0655 1.0000 0.0067
-13.750 -0.9390 0.04062 0.03722 -0.0669 1.0000 0.0069
-13.500 -0.9470 0.03696 0.03341 -0.0682 1.0000 0.0069
-13.250 -0.9537 0.03373 0.03003 -0.0689 1.0000 0.0069
-13.000 -0.9479 0.03206 0.02829 -0.0690 1.0000 0.0071
-12.750 -0.9541 0.02953 0.02562 -0.0683 1.0000 0.0071
-12.500 -0.9551 0.02788 0.02386 -0.0668 1.0000 0.0072
-12.250 -0.9601 0.02637 0.02225 -0.0640 1.0000 0.0072
-12.000 -0.9675 0.02531 0.02110 -0.0597 1.0000 0.0073
-11.750 -0.9680 0.02469 0.02040 -0.0556 1.0000 0.0074
-11.500 -0.9679 0.02353 0.01913 -0.0520 1.0000 0.0074
-11.250 -0.9596 0.02285 0.01837 -0.0493 1.0000 0.0075
-11.000 -0.9521 0.02202 0.01745 -0.0464 1.0000 0.0076
-10.750 -0.9545 0.02031 0.01559 -0.0423 1.0000 0.0078
-10.500 -0.9407 0.01914 0.01435 -0.0409 0.9994 0.0082
-10.250 -0.9090 0.01834 0.01349 -0.0426 0.9975 0.0085
-10.000 -0.8756 0.01775 0.01286 -0.0444 0.9957 0.0089
-9.750 -0.8419 0.01703 0.01208 -0.0463 0.9940 0.0092
-9.500 -0.8113 0.01642 0.01141 -0.0475 0.9912 0.0097
-9.250 -0.7776 0.01608 0.01101 -0.0490 0.9887 0.0102
-9.000 -0.7477 0.01477 0.00961 -0.0505 0.9858 0.0109
-8.750 -0.7126 0.01413 0.00894 -0.0525 0.9840 0.0115
-8.500 -0.6809 0.01366 0.00844 -0.0537 0.9806 0.0123
-8.250 -0.6494 0.01316 0.00789 -0.0547 0.9763 0.0130
-8.000 -0.6151 0.01254 0.00721 -0.0564 0.9729 0.0139
-7.750 -0.5867 0.01192 0.00656 -0.0569 0.9665 0.0151
-7.500 -0.5566 0.01152 0.00614 -0.0575 0.9580 0.0164
-7.250 -0.5275 0.01123 0.00580 -0.0579 0.9453 0.0174
-7.000 -0.4988 0.01062 0.00512 -0.0582 0.9278 0.0195
-6.750 -0.4709 0.01031 0.00473 -0.0583 0.9013 0.0213
-6.500 -0.4455 0.01012 0.00439 -0.0577 0.8707 0.0226
-6.250 -0.4222 0.00982 0.00398 -0.0568 0.8420 0.0262
-6.000 -0.3980 0.00962 0.00368 -0.0561 0.8161 0.0310
-5.500 -0.3505 0.00903 0.00309 -0.0546 0.7710 0.0653
-5.250 -0.3257 0.00879 0.00286 -0.0541 0.7517 0.0859
-5.000 -0.3006 0.00858 0.00265 -0.0537 0.7341 0.1080
-4.750 -0.2755 0.00833 0.00245 -0.0532 0.7179 0.1364
-4.500 -0.2502 0.00807 0.00226 -0.0529 0.7031 0.1689
-4.250 -0.2247 0.00781 0.00208 -0.0525 0.6895 0.2055
-4.000 -0.1991 0.00754 0.00192 -0.0522 0.6769 0.2477
-3.750 -0.1742 0.00720 0.00175 -0.0519 0.6654 0.3064
-3.500 -0.1486 0.00695 0.00163 -0.0515 0.6546 0.3613
-3.250 -0.1218 0.00680 0.00157 -0.0514 0.6446 0.4035
-3.000 -0.0946 0.00674 0.00153 -0.0512 0.6351 0.4296
-2.750 -0.0669 0.00672 0.00148 -0.0512 0.6261 0.4431
-2.500 -0.0389 0.00669 0.00144 -0.0511 0.6179 0.4559
-2.250 -0.0113 0.00669 0.00141 -0.0511 0.6097 0.4690
-2.000 0.0169 0.00668 0.00138 -0.0511 0.6023 0.4813
-1.750 0.0447 0.00668 0.00136 -0.0510 0.5950 0.4911
-1.500 0.0728 0.00667 0.00133 -0.0511 0.5882 0.4999
-1.250 0.1008 0.00668 0.00132 -0.0510 0.5812 0.5089
-1.000 0.1288 0.00667 0.00131 -0.0510 0.5751 0.5179
-0.750 0.1570 0.00668 0.00130 -0.0511 0.5686 0.5270
-0.500 0.1847 0.00669 0.00130 -0.0510 0.5625 0.5367
-0.250 0.2130 0.00667 0.00130 -0.0511 0.5565 0.5458
0.000 0.2409 0.00670 0.00130 -0.0511 0.5506 0.5558
0.250 0.2689 0.00669 0.00132 -0.0510 0.5450 0.5664
0.500 0.2969 0.00668 0.00133 -0.0511 0.5389 0.5776
0.750 0.3245 0.00672 0.00136 -0.0510 0.5333 0.5896
1.000 0.3527 0.00670 0.00138 -0.0510 0.5280 0.6027
1.250 0.3804 0.00670 0.00141 -0.0510 0.5221 0.6165
1.500 0.4080 0.00672 0.00145 -0.0509 0.5167 0.6311
1.750 0.4359 0.00670 0.00149 -0.0509 0.5112 0.6470
2.000 0.4633 0.00672 0.00154 -0.0509 0.5053 0.6646
2.250 0.4908 0.00671 0.00159 -0.0508 0.4997 0.6841
2.500 0.5181 0.00670 0.00165 -0.0506 0.4931 0.7056
2.750 0.5450 0.00671 0.00171 -0.0504 0.4863 0.7294
3.000 0.5721 0.00669 0.00178 -0.0503 0.4791 0.7571
3.250 0.5982 0.00669 0.00186 -0.0499 0.4723 0.7875
3.500 0.6245 0.00665 0.00194 -0.0495 0.4654 0.8208
3.750 0.6493 0.00666 0.00204 -0.0488 0.4580 0.8586
4.000 0.6740 0.00661 0.00214 -0.0479 0.4510 0.9024
4.250 0.7009 0.00667 0.00226 -0.0476 0.4429 0.9461
4.500 0.7353 0.00675 0.00236 -0.0489 0.4339 0.9706
4.750 0.7718 0.00687 0.00247 -0.0509 0.4243 0.9834
5.000 0.8103 0.00702 0.00259 -0.0533 0.4131 0.9902
5.250 0.8476 0.00715 0.00270 -0.0555 0.4014 0.9963
5.500 0.8826 0.00730 0.00283 -0.0572 0.3886 1.0000
5.750 0.9053 0.00745 0.00296 -0.0562 0.3762 1.0000
6.000 0.9281 0.00763 0.00310 -0.0553 0.3631 1.0000
6.250 0.9505 0.00783 0.00326 -0.0543 0.3469 1.0000
6.500 0.9721 0.00811 0.00346 -0.0531 0.3262 1.0000
6.750 0.9925 0.00849 0.00370 -0.0518 0.2954 1.0000
7.000 1.0121 0.00895 0.00400 -0.0505 0.2597 1.0000
7.250 1.0306 0.00951 0.00438 -0.0489 0.2232 1.0000
7.500 1.0498 0.01004 0.00476 -0.0476 0.1928 1.0000
7.750 1.0686 0.01059 0.00516 -0.0462 0.1636 1.0000
8.000 1.0872 0.01116 0.00559 -0.0447 0.1370 1.0000
8.250 1.1055 0.01173 0.00602 -0.0433 0.1134 1.0000
8.500 1.1240 0.01227 0.00647 -0.0419 0.0933 1.0000
8.750 1.1419 0.01282 0.00693 -0.0404 0.0770 1.0000
9.000 1.1604 0.01332 0.00737 -0.0390 0.0652 1.0000
9.250 1.1783 0.01382 0.00783 -0.0375 0.0548 1.0000
9.500 1.1956 0.01433 0.00830 -0.0359 0.0459 1.0000
9.750 1.2118 0.01486 0.00881 -0.0341 0.0383 1.0000
10.000 1.2252 0.01542 0.00933 -0.0319 0.0318 1.0000
10.250 1.2364 0.01598 0.00987 -0.0292 0.0270 1.0000
10.500 1.2485 0.01652 0.01043 -0.0268 0.0234 1.0000
10.750 1.2580 0.01721 0.01111 -0.0241 0.0199 1.0000
11.000 1.2704 0.01780 0.01173 -0.0220 0.0180 1.0000
11.250 1.2789 0.01860 0.01254 -0.0195 0.0158 1.0000
11.500 1.2897 0.01931 0.01331 -0.0174 0.0144 1.0000
11.750 1.2988 0.02016 0.01420 -0.0153 0.0131 1.0000
12.000 1.3033 0.02133 0.01540 -0.0128 0.0115 1.0000
12.250 1.3130 0.02226 0.01640 -0.0112 0.0109 1.0000
12.500 1.3206 0.02339 0.01758 -0.0095 0.0102 1.0000
12.750 1.3237 0.02493 0.01916 -0.0077 0.0092 1.0000
13.000 1.3261 0.02665 0.02096 -0.0062 0.0087 1.0000
13.250 1.3349 0.02797 0.02234 -0.0052 0.0082 1.0000
13.500 1.3413 0.02955 0.02400 -0.0043 0.0077 1.0000
13.750 1.3451 0.03145 0.02596 -0.0035 0.0075 1.0000
14.000 1.3492 0.03338 0.02795 -0.0029 0.0070 1.0000
14.250 1.3500 0.03571 0.03036 -0.0024 0.0069 1.0000
14.500 1.3452 0.03870 0.03344 -0.0019 0.0066 1.0000
14.750 1.3451 0.04130 0.03613 -0.0017 0.0063 1.0000
15.000 1.3448 0.04399 0.03892 -0.0017 0.0062 1.0000
15.250 1.3448 0.04672 0.04173 -0.0018 0.0061 1.0000
15.500 1.3475 0.04920 0.04429 -0.0020 0.0059 1.0000
15.750 1.3457 0.05230 0.04748 -0.0023 0.0058 1.0000
16.000 1.3425 0.05564 0.05090 -0.0028 0.0056 1.0000
16.250 1.3397 0.05904 0.05440 -0.0035 0.0055 1.0000
16.500 1.3373 0.06250 0.05794 -0.0043 0.0054 1.0000
16.750 1.3316 0.06650 0.06205 -0.0054 0.0054 1.0000
17.000 1.3270 0.07044 0.06608 -0.0065 0.0053 1.0000
17.250 1.3213 0.07467 0.07040 -0.0079 0.0052 1.0000
17.500 1.3174 0.07872 0.07453 -0.0093 0.0051 1.0000
17.750 1.3066 0.08393 0.07985 -0.0113 0.0050 1.0000
18.000 1.2991 0.08876 0.08477 -0.0132 0.0049 1.0000
18.250 1.2832 0.09511 0.09123 -0.0159 0.0048 1.0000
18.500 1.2778 0.09983 0.09605 -0.0180 0.0048 1.0000
18.750 1.2639 0.10610 0.10244 -0.0208 0.0048 1.0000
19.000 1.2513 0.11232 0.10877 -0.0238 0.0047 1.0000
19.250 1.2451 0.11750 0.11404 -0.0264 0.0047 1.0000
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Polar data table (+)
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