EPPLER 864 STRUT AIRFOIL (e864-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 864 STRUT AIRFOIL (e864-il) Reynolds number: 1,000,000 Max Cl/Cd: 46.65 at α=8.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e864-il-1000000-n5.txt Download as CSV file: xf-e864-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 864 STRUT AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-18.750 -1.0518 0.09524 0.08992 -0.0066 0.5550 0.2283
-18.500 -1.0505 0.09263 0.08730 -0.0071 0.5493 0.2323
-18.250 -1.0509 0.08981 0.08444 -0.0076 0.5445 0.2361
-18.000 -1.0452 0.08760 0.08218 -0.0082 0.5382 0.2391
-17.750 -1.0473 0.08470 0.07926 -0.0086 0.5323 0.2435
-17.500 -1.0477 0.08194 0.07647 -0.0089 0.5262 0.2475
-17.250 -1.0459 0.07941 0.07389 -0.0093 0.5226 0.2508
-17.000 -1.0474 0.07663 0.07110 -0.0096 0.5188 0.2549
-16.750 -1.0547 0.07329 0.06774 -0.0096 0.5152 0.2595
-16.500 -1.0515 0.07094 0.06534 -0.0100 0.5109 0.2629
-16.250 -1.0507 0.06842 0.06278 -0.0102 0.5065 0.2664
-15.750 -1.0609 0.06239 0.05670 -0.0101 0.5006 0.2749
-15.500 -1.0638 0.05958 0.05384 -0.0101 0.4981 0.2781
-15.250 -1.0730 0.05634 0.05059 -0.0097 0.4957 0.2825
-15.000 -1.0813 0.05315 0.04736 -0.0094 0.4930 0.2868
-14.750 -1.0759 0.05116 0.04531 -0.0095 0.4897 0.2897
-14.500 -1.0876 0.04778 0.04190 -0.0089 0.4871 0.2937
-14.250 -1.0917 0.04511 0.03920 -0.0086 0.4840 0.2977
-13.750 -1.0850 0.04093 0.03491 -0.0083 0.4788 0.3037
-13.500 -1.0937 0.03798 0.03194 -0.0076 0.4771 0.3075
-13.250 -1.0970 0.03548 0.02942 -0.0070 0.4750 0.3111
-13.000 -1.0891 0.03387 0.02776 -0.0069 0.4723 0.3141
-12.750 -1.0804 0.03228 0.02612 -0.0068 0.4696 0.3166
-12.500 -1.0728 0.03070 0.02449 -0.0066 0.4669 0.3192
-12.250 -1.0705 0.02876 0.02253 -0.0061 0.4645 0.3224
-12.000 -1.0603 0.02742 0.02115 -0.0059 0.4617 0.3253
-11.750 -1.0481 0.02621 0.01990 -0.0058 0.4590 0.3278
-11.500 -1.0315 0.02531 0.01896 -0.0059 0.4578 0.3300
-11.250 -1.0166 0.02430 0.01791 -0.0059 0.4564 0.3319
-11.000 -1.0051 0.02316 0.01676 -0.0055 0.4549 0.3344
-10.750 -0.9923 0.02212 0.01571 -0.0052 0.4532 0.3369
-10.500 -0.9754 0.02135 0.01491 -0.0052 0.4513 0.3392
-10.250 -0.9578 0.02062 0.01415 -0.0051 0.4494 0.3413
-10.000 -0.9373 0.02008 0.01357 -0.0053 0.4475 0.3431
-9.750 -0.9161 0.01958 0.01302 -0.0054 0.4454 0.3447
-9.500 -0.8968 0.01902 0.01242 -0.0054 0.4431 0.3463
-9.250 -0.8796 0.01841 0.01178 -0.0051 0.4406 0.3484
-9.000 -0.8618 0.01784 0.01120 -0.0047 0.4387 0.3503
-8.750 -0.8414 0.01739 0.01074 -0.0046 0.4378 0.3522
-8.500 -0.8205 0.01698 0.01032 -0.0045 0.4367 0.3540
-8.250 -0.7986 0.01663 0.00994 -0.0045 0.4356 0.3556
-8.000 -0.7755 0.01633 0.00962 -0.0046 0.4343 0.3571
-7.750 -0.7522 0.01605 0.00931 -0.0047 0.4330 0.3585
-7.500 -0.7285 0.01581 0.00903 -0.0048 0.4316 0.3596
-7.250 -0.7056 0.01554 0.00874 -0.0047 0.4302 0.3608
-7.000 -0.6854 0.01522 0.00841 -0.0043 0.4288 0.3625
-6.750 -0.6641 0.01495 0.00812 -0.0039 0.4273 0.3641
-6.500 -0.6420 0.01472 0.00788 -0.0036 0.4258 0.3656
-6.250 -0.6197 0.01452 0.00766 -0.0033 0.4243 0.3671
-6.000 -0.5964 0.01435 0.00748 -0.0032 0.4226 0.3685
-5.750 -0.5728 0.01421 0.00731 -0.0030 0.4207 0.3698
-5.500 -0.5489 0.01406 0.00714 -0.0029 0.4197 0.3710
-5.250 -0.5246 0.01392 0.00699 -0.0027 0.4189 0.3722
-5.000 -0.4998 0.01380 0.00685 -0.0027 0.4181 0.3733
-4.750 -0.4756 0.01369 0.00673 -0.0025 0.4172 0.3743
-4.500 -0.4523 0.01361 0.00663 -0.0021 0.4163 0.3750
-4.250 -0.4316 0.01352 0.00652 -0.0012 0.4153 0.3761
-4.000 -0.4145 0.01343 0.00644 0.0004 0.4143 0.3774
-3.750 -0.3972 0.01337 0.00638 0.0019 0.4132 0.3788
-3.500 -0.3746 0.01331 0.00631 0.0025 0.4121 0.3802
-3.250 -0.3503 0.01326 0.00626 0.0028 0.4108 0.3815
-3.000 -0.3251 0.01322 0.00621 0.0029 0.4095 0.3828
-2.750 -0.2994 0.01319 0.00617 0.0029 0.4081 0.3840
-2.500 -0.2733 0.01318 0.00614 0.0029 0.4067 0.3851
-2.250 -0.2468 0.01317 0.00611 0.0027 0.4053 0.3861
-2.000 -0.2202 0.01317 0.00610 0.0026 0.4039 0.3872
-1.750 -0.1933 0.01319 0.00610 0.0024 0.4025 0.3883
-1.500 -0.1654 0.01317 0.00608 0.0020 0.4019 0.3892
-1.250 -0.1372 0.01315 0.00606 0.0016 0.4012 0.3901
-1.000 -0.1089 0.01314 0.00603 0.0012 0.4001 0.3908
-0.750 -0.0807 0.01312 0.00601 0.0007 0.3988 0.3914
-0.500 -0.0537 0.01307 0.00597 0.0005 0.3974 0.3928
-0.250 -0.0266 0.01303 0.00595 0.0003 0.3960 0.3943
0.000 0.0006 0.01301 0.00594 0.0000 0.3948 0.3958
0.250 0.0279 0.01300 0.00593 -0.0002 0.3935 0.3971
0.500 0.0552 0.01301 0.00594 -0.0005 0.3919 0.3983
0.750 0.0824 0.01302 0.00594 -0.0007 0.3902 0.3995
1.000 0.1091 0.01305 0.00596 -0.0009 0.3883 0.4006
1.250 0.1356 0.01309 0.00600 -0.0010 0.3867 0.4017
1.500 0.1628 0.01312 0.00603 -0.0013 0.3856 0.4029
1.750 0.1906 0.01314 0.00605 -0.0017 0.3849 0.4040
2.000 0.2183 0.01315 0.00608 -0.0020 0.3841 0.4051
2.250 0.2458 0.01317 0.00611 -0.0023 0.3830 0.4060
2.500 0.2730 0.01320 0.00614 -0.0025 0.3818 0.4067
2.750 0.2997 0.01323 0.00617 -0.0027 0.3805 0.4074
3.000 0.3260 0.01327 0.00621 -0.0028 0.3792 0.4079
3.250 0.3511 0.01330 0.00625 -0.0026 0.3779 0.4090
3.500 0.3753 0.01332 0.00629 -0.0024 0.3767 0.4107
3.750 0.3977 0.01336 0.00634 -0.0018 0.3753 0.4123
4.000 0.4151 0.01340 0.00639 -0.0002 0.3739 0.4138
4.250 0.4320 0.01347 0.00646 0.0015 0.3724 0.4151
4.500 0.4503 0.01358 0.00658 0.0027 0.3706 0.4163
4.750 0.4733 0.01368 0.00670 0.0031 0.3695 0.4175
5.000 0.4977 0.01378 0.00683 0.0033 0.3685 0.4187
5.250 0.5223 0.01390 0.00697 0.0034 0.3672 0.4199
5.500 0.5463 0.01404 0.00713 0.0035 0.3658 0.4210
5.750 0.5701 0.01420 0.00730 0.0037 0.3642 0.4221
6.000 0.5936 0.01438 0.00749 0.0038 0.3623 0.4232
6.250 0.6161 0.01459 0.00771 0.0041 0.3605 0.4241
6.500 0.6376 0.01485 0.00796 0.0045 0.3586 0.4250
6.750 0.6588 0.01513 0.00824 0.0049 0.3566 0.4258
7.000 0.6801 0.01542 0.00854 0.0052 0.3547 0.4272
7.250 0.7039 0.01562 0.00879 0.0051 0.3531 0.4292
7.500 0.7273 0.01586 0.00906 0.0051 0.3511 0.4310
7.750 0.7493 0.01616 0.00939 0.0052 0.3490 0.4326
8.000 0.7701 0.01653 0.00977 0.0054 0.3467 0.4342
8.250 0.7903 0.01694 0.01020 0.0056 0.3444 0.4358
8.500 0.8077 0.01749 0.01075 0.0061 0.3420 0.4373
8.750 0.8281 0.01795 0.01124 0.0062 0.3400 0.4388
9.000 0.8495 0.01839 0.01171 0.0061 0.3380 0.4403
9.250 0.8694 0.01891 0.01226 0.0062 0.3356 0.4417
9.500 0.8885 0.01950 0.01286 0.0062 0.3330 0.4430
9.750 0.9044 0.02028 0.01366 0.0065 0.3304 0.4441
10.000 0.9190 0.02116 0.01454 0.0069 0.3278 0.4450
10.250 0.9349 0.02200 0.01541 0.0070 0.3256 0.4468
10.500 0.9532 0.02271 0.01617 0.0069 0.3234 0.4496
10.750 0.9675 0.02370 0.01720 0.0070 0.3206 0.4522
11.000 0.9800 0.02482 0.01835 0.0072 0.3173 0.4545
11.250 0.9852 0.02647 0.02002 0.0078 0.3138 0.4565
11.500 0.9961 0.02779 0.02138 0.0080 0.3108 0.4585
11.750 1.0068 0.02914 0.02276 0.0081 0.3075 0.4604
12.000 1.0088 0.03113 0.02479 0.0087 0.3033 0.4620
12.250 1.0043 0.03364 0.02731 0.0094 0.2992 0.4634
12.500 1.0125 0.03526 0.02897 0.0095 0.2960 0.4648
13.000 1.0039 0.04048 0.03426 0.0107 0.2878 0.4684
13.250 1.0021 0.04296 0.03678 0.0111 0.2842 0.4710
13.500 0.9963 0.04583 0.03969 0.0115 0.2793 0.4734
13.750 0.9753 0.04993 0.04382 0.0125 0.2733 0.4752
14.000 0.9775 0.05221 0.04614 0.0126 0.2696 0.4777
14.250 0.9641 0.05585 0.04981 0.0131 0.2636 0.4797
14.500 0.9540 0.05920 0.05318 0.0135 0.2583 0.4817
14.750 0.9460 0.06248 0.05649 0.0137 0.2528 0.4837
15.000 0.9292 0.06659 0.06060 0.0141 0.2465 0.4854
15.250 0.9262 0.06947 0.06350 0.0140 0.2408 0.4872
15.500 0.9078 0.07382 0.06786 0.0143 0.2334 0.4897
15.750 0.9038 0.07690 0.07095 0.0141 0.2265 0.4934
16.000 0.8911 0.08083 0.07489 0.0141 0.2193 0.4964
16.250 0.8819 0.08448 0.07853 0.0140 0.2114 0.4993
16.500 0.8779 0.08765 0.08171 0.0136 0.2040 0.5025
16.750 0.8641 0.09188 0.08592 0.0134 0.1950 0.5049
17.000 0.8548 0.09566 0.08967 0.0131 0.1856 0.5073
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