E209 (13.72%) (e209-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: E209 (13.72%) (e209-il) Reynolds number: 1,000,000 Max Cl/Cd: 103.66 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e209-il-1000000-n5.txt Download as CSV file: xf-e209-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.500 -0.8478 0.11135 0.10890 -0.0284 1.0000 0.0039
-17.250 -0.8802 0.10124 0.09868 -0.0335 1.0000 0.0039
-17.000 -0.9185 0.09026 0.08754 -0.0393 1.0000 0.0038
-16.750 -0.9454 0.08160 0.07875 -0.0439 1.0000 0.0037
-16.500 -0.9749 0.07270 0.06970 -0.0488 1.0000 0.0038
-16.250 -1.0052 0.06421 0.06106 -0.0537 1.0000 0.0038
-16.000 -1.0083 0.06035 0.05710 -0.0556 1.0000 0.0036
-15.750 -1.0339 0.05335 0.04995 -0.0595 1.0000 0.0037
-15.500 -1.0431 0.04892 0.04541 -0.0618 1.0000 0.0037
-15.250 -1.0605 0.04356 0.03991 -0.0646 1.0000 0.0038
-15.000 -1.0689 0.03954 0.03576 -0.0665 1.0000 0.0038
-14.750 -1.0722 0.03631 0.03243 -0.0678 1.0000 0.0038
-14.500 -1.0752 0.03331 0.02931 -0.0688 1.0000 0.0038
-14.250 -1.0779 0.03060 0.02649 -0.0692 1.0000 0.0039
-14.000 -1.0777 0.02850 0.02429 -0.0691 1.0000 0.0040
-13.750 -1.0788 0.02661 0.02230 -0.0681 1.0000 0.0040
-13.500 -1.0791 0.02514 0.02074 -0.0663 1.0000 0.0041
-13.250 -1.0781 0.02408 0.01961 -0.0638 1.0000 0.0042
-13.000 -1.0809 0.02321 0.01868 -0.0599 1.0000 0.0043
-12.750 -1.0820 0.02245 0.01785 -0.0558 1.0000 0.0043
-12.500 -1.0753 0.02170 0.01703 -0.0530 1.0000 0.0044
-12.250 -1.0678 0.02094 0.01621 -0.0502 1.0000 0.0045
-12.000 -1.0425 0.02015 0.01534 -0.0508 0.9985 0.0047
-11.750 -1.0162 0.01931 0.01442 -0.0517 0.9964 0.0048
-11.500 -0.9884 0.01861 0.01366 -0.0526 0.9944 0.0051
-11.250 -0.9631 0.01786 0.01283 -0.0530 0.9918 0.0052
-11.000 -0.9365 0.01721 0.01211 -0.0535 0.9890 0.0053
-10.750 -0.9079 0.01661 0.01146 -0.0544 0.9864 0.0055
-10.500 -0.8781 0.01592 0.01069 -0.0555 0.9842 0.0057
-10.250 -0.8500 0.01529 0.01001 -0.0562 0.9813 0.0061
-10.000 -0.8242 0.01477 0.00946 -0.0563 0.9762 0.0064
-9.750 -0.7944 0.01430 0.00897 -0.0572 0.9718 0.0070
-9.500 -0.7675 0.01386 0.00849 -0.0574 0.9653 0.0075
-9.000 -0.7088 0.01296 0.00749 -0.0587 0.9433 0.0085
-8.750 -0.6782 0.01254 0.00702 -0.0595 0.9196 0.0094
-8.500 -0.6522 0.01228 0.00661 -0.0593 0.8842 0.0102
-8.250 -0.6290 0.01209 0.00627 -0.0584 0.8507 0.0108
-8.000 -0.6060 0.01189 0.00592 -0.0575 0.8221 0.0114
-7.750 -0.5827 0.01164 0.00557 -0.0568 0.7963 0.0124
-7.500 -0.5587 0.01145 0.00527 -0.0561 0.7732 0.0133
-7.250 -0.5339 0.01128 0.00500 -0.0556 0.7532 0.0143
-7.000 -0.5088 0.01112 0.00475 -0.0552 0.7351 0.0151
-6.750 -0.4841 0.01088 0.00442 -0.0546 0.7180 0.0165
-6.500 -0.4588 0.01068 0.00415 -0.0542 0.7029 0.0178
-6.250 -0.4329 0.01050 0.00390 -0.0539 0.6889 0.0189
-6.000 -0.4070 0.01032 0.00366 -0.0536 0.6754 0.0209
-5.750 -0.3812 0.01011 0.00342 -0.0533 0.6633 0.0245
-5.500 -0.3554 0.00989 0.00318 -0.0530 0.6523 0.0313
-5.250 -0.3295 0.00967 0.00296 -0.0527 0.6418 0.0427
-5.000 -0.3034 0.00945 0.00276 -0.0524 0.6316 0.0555
-4.750 -0.2771 0.00924 0.00257 -0.0522 0.6232 0.0687
-4.500 -0.2507 0.00906 0.00240 -0.0520 0.6142 0.0832
-4.250 -0.2240 0.00887 0.00224 -0.0519 0.6063 0.1008
-3.750 -0.1710 0.00845 0.00193 -0.0515 0.5914 0.1496
-3.500 -0.1448 0.00820 0.00179 -0.0513 0.5840 0.1852
-3.250 -0.1182 0.00797 0.00166 -0.0512 0.5776 0.2207
-3.000 -0.0916 0.00777 0.00154 -0.0510 0.5710 0.2545
-2.750 -0.0654 0.00749 0.00142 -0.0509 0.5650 0.3057
-2.500 -0.0388 0.00727 0.00133 -0.0507 0.5586 0.3518
-2.250 -0.0118 0.00715 0.00128 -0.0506 0.5528 0.3862
-2.000 0.0160 0.00706 0.00125 -0.0506 0.5473 0.4140
-1.750 0.0438 0.00703 0.00122 -0.0506 0.5410 0.4291
-1.500 0.0720 0.00702 0.00120 -0.0506 0.5358 0.4403
-1.250 0.1001 0.00699 0.00118 -0.0506 0.5304 0.4512
-1.000 0.1280 0.00699 0.00117 -0.0506 0.5246 0.4613
-0.500 0.1843 0.00698 0.00116 -0.0507 0.5141 0.4808
-0.250 0.2123 0.00699 0.00116 -0.0507 0.5088 0.4890
0.000 0.2405 0.00699 0.00117 -0.0508 0.5037 0.4982
0.250 0.2686 0.00699 0.00118 -0.0508 0.4982 0.5072
0.750 0.3246 0.00701 0.00121 -0.0508 0.4880 0.5261
1.000 0.3526 0.00702 0.00124 -0.0508 0.4825 0.5352
1.250 0.3805 0.00705 0.00127 -0.0508 0.4777 0.5446
1.500 0.4086 0.00706 0.00130 -0.0509 0.4725 0.5532
2.000 0.4643 0.00712 0.00139 -0.0509 0.4615 0.5711
2.250 0.4922 0.00714 0.00144 -0.0509 0.4553 0.5810
2.750 0.5473 0.00723 0.00156 -0.0508 0.4399 0.6037
3.000 0.5746 0.00728 0.00163 -0.0507 0.4316 0.6157
3.250 0.6019 0.00733 0.00171 -0.0506 0.4229 0.6293
3.500 0.6291 0.00738 0.00179 -0.0505 0.4147 0.6452
4.000 0.6829 0.00750 0.00198 -0.0502 0.3957 0.6806
4.250 0.7095 0.00757 0.00209 -0.0500 0.3850 0.6999
4.500 0.7357 0.00765 0.00221 -0.0498 0.3738 0.7226
4.750 0.7615 0.00774 0.00235 -0.0494 0.3613 0.7484
5.250 0.8114 0.00794 0.00265 -0.0484 0.3306 0.8094
5.500 0.8349 0.00809 0.00284 -0.0476 0.3101 0.8454
5.750 0.8562 0.00828 0.00307 -0.0463 0.2858 0.8904
6.000 0.8801 0.00849 0.00332 -0.0455 0.2636 0.9451
6.250 0.9130 0.00895 0.00364 -0.0470 0.2303 0.9760
6.500 0.9442 0.00949 0.00401 -0.0482 0.1942 0.9917
6.750 0.9689 0.01007 0.00441 -0.0481 0.1609 1.0000
7.000 0.9878 0.01059 0.00478 -0.0466 0.1320 1.0000
7.250 1.0089 0.01098 0.00510 -0.0456 0.1153 1.0000
7.500 1.0301 0.01137 0.00542 -0.0445 0.1008 1.0000
7.750 1.0505 0.01179 0.00578 -0.0434 0.0862 1.0000
8.000 1.0707 0.01223 0.00615 -0.0422 0.0728 1.0000
8.250 1.0897 0.01273 0.00657 -0.0409 0.0590 1.0000
8.500 1.1104 0.01310 0.00692 -0.0398 0.0517 1.0000
8.750 1.1290 0.01359 0.00736 -0.0384 0.0420 1.0000
9.000 1.1472 0.01407 0.00781 -0.0369 0.0340 1.0000
9.250 1.1654 0.01453 0.00824 -0.0355 0.0290 1.0000
9.500 1.1832 0.01498 0.00869 -0.0340 0.0248 1.0000
9.750 1.1988 0.01545 0.00915 -0.0321 0.0209 1.0000
10.000 1.2125 0.01591 0.00962 -0.0299 0.0185 1.0000
10.250 1.2257 0.01640 0.01012 -0.0276 0.0163 1.0000
10.500 1.2392 0.01690 0.01065 -0.0255 0.0148 1.0000
10.750 1.2510 0.01750 0.01126 -0.0232 0.0130 1.0000
11.000 1.2640 0.01806 0.01186 -0.0212 0.0119 1.0000
11.250 1.2761 0.01869 0.01252 -0.0192 0.0110 1.0000
11.500 1.2862 0.01945 0.01330 -0.0171 0.0098 1.0000
11.750 1.2973 0.02020 0.01409 -0.0152 0.0089 1.0000
12.000 1.3069 0.02106 0.01500 -0.0134 0.0079 1.0000
12.250 1.3151 0.02207 0.01604 -0.0115 0.0070 1.0000
12.500 1.3238 0.02312 0.01715 -0.0099 0.0063 1.0000
12.750 1.3317 0.02430 0.01837 -0.0085 0.0057 1.0000
13.000 1.3380 0.02567 0.01979 -0.0071 0.0051 1.0000
13.250 1.3444 0.02712 0.02130 -0.0059 0.0048 1.0000
13.500 1.3517 0.02858 0.02282 -0.0050 0.0046 1.0000
13.750 1.3580 0.03019 0.02450 -0.0042 0.0043 1.0000
14.000 1.3633 0.03198 0.02635 -0.0035 0.0041 1.0000
14.250 1.3675 0.03392 0.02835 -0.0029 0.0039 1.0000
14.500 1.3707 0.03603 0.03053 -0.0024 0.0037 1.0000
14.750 1.3749 0.03810 0.03267 -0.0021 0.0037 1.0000
15.000 1.3753 0.04060 0.03526 -0.0019 0.0035 1.0000
15.250 1.3757 0.04318 0.03792 -0.0018 0.0033 1.0000
15.500 1.3753 0.04590 0.04072 -0.0018 0.0032 1.0000
15.750 1.3764 0.04854 0.04343 -0.0020 0.0031 1.0000
16.000 1.3762 0.05140 0.04639 -0.0022 0.0030 1.0000
16.250 1.3753 0.05441 0.04949 -0.0027 0.0030 1.0000
16.500 1.3733 0.05765 0.05281 -0.0032 0.0030 1.0000
16.750 1.3727 0.06080 0.05605 -0.0039 0.0030 1.0000
17.000 1.3697 0.06436 0.05970 -0.0048 0.0029 1.0000
17.250 1.3672 0.06792 0.06334 -0.0058 0.0028 1.0000
17.500 1.3637 0.07172 0.06724 -0.0069 0.0027 1.0000
17.750 1.3589 0.07581 0.07142 -0.0083 0.0027 1.0000
18.000 1.3539 0.08002 0.07573 -0.0098 0.0026 1.0000
18.250 1.3459 0.08480 0.08061 -0.0116 0.0027 1.0000
18.500 1.3405 0.08926 0.08517 -0.0134 0.0026 1.0000
18.750 1.3338 0.09405 0.09006 -0.0154 0.0025 1.0000
19.000 1.3247 0.09933 0.09545 -0.0177 0.0026 1.0000
19.250 1.3139 0.10502 0.10126 -0.0204 0.0025 1.0000
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Polar data table (+)
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