EPPLER 664 AIRFOIL (e664-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 664 AIRFOIL (e664-il) Reynolds number: 50,000 Max Cl/Cd: 19.73 at α=12° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e664-il-50000-n5.txt Download as CSV file: xf-e664-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 664 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.750 -0.3708 0.13092 0.12403 -0.0605 1.0000 0.0502
-12.500 -0.3780 0.12924 0.12244 -0.0583 1.0000 0.0498
-12.250 -0.3897 0.12755 0.12086 -0.0560 1.0000 0.0494
-12.000 -0.4019 0.12576 0.11915 -0.0538 1.0000 0.0490
-11.750 -0.4064 0.12198 0.11542 -0.0549 0.9978 0.0487
-11.500 -0.4036 0.11627 0.10971 -0.0592 0.9929 0.0485
-11.250 -0.4019 0.11066 0.10412 -0.0633 0.9878 0.0480
-11.000 -0.4039 0.10414 0.09760 -0.0684 0.9832 0.0477
-10.750 -0.4109 0.09709 0.09054 -0.0736 0.9774 0.0471
-10.500 -0.4253 0.08944 0.08284 -0.0797 0.9723 0.0465
-10.250 -0.4483 0.08319 0.07651 -0.0831 0.9650 0.0452
-10.000 -0.4721 0.07742 0.07055 -0.0860 0.9589 0.0446
-9.750 -0.4976 0.07375 0.06672 -0.0850 0.9505 0.0441
-9.500 -0.5152 0.07032 0.06306 -0.0844 0.9446 0.0440
-9.250 -0.5374 0.06827 0.06085 -0.0804 0.9366 0.0440
-9.000 -0.5463 0.06523 0.05753 -0.0787 0.9312 0.0442
-8.750 -0.5576 0.06271 0.05475 -0.0755 0.9251 0.0442
-8.500 -0.5631 0.06039 0.05217 -0.0727 0.9194 0.0447
-8.250 -0.5605 0.05772 0.04916 -0.0710 0.9154 0.0452
-8.000 -0.5593 0.05533 0.04641 -0.0686 0.9116 0.0458
-7.750 -0.5616 0.05344 0.04423 -0.0649 0.9064 0.0460
-7.500 -0.5529 0.05113 0.04153 -0.0629 0.9025 0.0465
-7.250 -0.5361 0.04876 0.03874 -0.0619 0.8996 0.0473
-7.000 -0.5129 0.04651 0.03603 -0.0618 0.8974 0.0484
-6.750 -0.5040 0.04516 0.03436 -0.0588 0.8935 0.0493
-6.500 -0.4874 0.04379 0.03277 -0.0572 0.8900 0.0513
-6.250 -0.4662 0.04273 0.03165 -0.0566 0.8869 0.0546
-6.000 -0.4363 0.04158 0.03026 -0.0569 0.8847 0.0587
-5.750 -0.3998 0.04044 0.02899 -0.0579 0.8830 0.0631
-5.500 -0.3635 0.03962 0.02800 -0.0590 0.8815 0.0717
-5.250 -0.3505 0.03910 0.02754 -0.0567 0.8778 0.0792
-5.000 -0.3397 0.03857 0.02701 -0.0540 0.8737 0.0909
-4.750 -0.3245 0.03787 0.02635 -0.0522 0.8702 0.1127
-4.500 -0.3101 0.03690 0.02575 -0.0507 0.8672 0.1537
-4.250 -0.2986 0.03559 0.02507 -0.0488 0.8645 0.2321
-4.000 -0.2762 0.03566 0.02759 -0.0434 0.8623 0.5662
-3.500 -0.2805 0.03770 0.02938 -0.0308 0.8522 0.7431
-3.250 -0.2685 0.03876 0.03016 -0.0268 0.8488 0.7855
-3.000 -0.2518 0.03996 0.03113 -0.0231 0.8448 0.8159
-2.500 -0.0885 0.04261 0.03285 -0.0380 0.8439 0.8920
-2.250 -0.0422 0.04270 0.03266 -0.0418 0.8409 0.9073
-2.000 0.0000 0.04264 0.03236 -0.0453 0.8377 0.9175
-1.750 0.0363 0.04255 0.03205 -0.0478 0.8347 0.9250
-1.250 0.0801 0.04267 0.03188 -0.0479 0.8260 0.9378
-1.000 0.1021 0.04274 0.03182 -0.0481 0.8213 0.9430
-0.750 0.1256 0.04280 0.03175 -0.0482 0.8175 0.9478
-0.500 0.1647 0.04273 0.03153 -0.0512 0.8149 0.9506
-0.250 0.1646 0.04312 0.03189 -0.0477 0.8070 0.9556
0.000 0.1867 0.04325 0.03192 -0.0477 0.8023 0.9592
0.250 0.2184 0.04328 0.03186 -0.0492 0.7991 0.9616
0.750 0.2480 0.04383 0.03231 -0.0471 0.7860 0.9677
1.000 0.2804 0.04387 0.03229 -0.0486 0.7825 0.9697
1.250 0.2774 0.04440 0.03282 -0.0446 0.7732 0.9732
1.500 0.3066 0.04450 0.03287 -0.0456 0.7684 0.9748
1.750 0.3239 0.04482 0.03318 -0.0449 0.7618 0.9771
2.000 0.3398 0.04513 0.03349 -0.0440 0.7546 0.9794
2.250 0.3706 0.04518 0.03352 -0.0450 0.7504 0.9807
2.500 0.3713 0.04578 0.03414 -0.0418 0.7406 0.9836
2.750 0.4008 0.04588 0.03423 -0.0427 0.7355 0.9851
3.000 0.4099 0.04638 0.03477 -0.0408 0.7265 0.9871
3.250 0.4345 0.04652 0.03493 -0.0410 0.7203 0.9885
3.500 0.4483 0.04695 0.03539 -0.0397 0.7119 0.9908
3.750 0.4701 0.04717 0.03565 -0.0394 0.7047 0.9928
4.000 0.4847 0.04756 0.03609 -0.0382 0.6963 0.9947
4.250 0.5051 0.04775 0.03634 -0.0377 0.6887 0.9963
4.500 0.5174 0.04821 0.03686 -0.0363 0.6793 0.9985
4.750 0.5425 0.04827 0.03698 -0.0363 0.6724 1.0000
5.000 0.5407 0.04879 0.03756 -0.0324 0.6614 1.0000
5.250 0.5651 0.04857 0.03740 -0.0318 0.6557 1.0000
5.500 0.5606 0.04913 0.03800 -0.0276 0.6437 1.0000
6.000 0.5836 0.04926 0.03826 -0.0231 0.6263 1.0000
6.250 0.5817 0.04971 0.03879 -0.0194 0.6145 1.0000
6.750 0.6052 0.04961 0.03884 -0.0147 0.5966 1.0000
7.000 0.6041 0.05004 0.03933 -0.0111 0.5847 1.0000
7.500 0.6288 0.04975 0.03922 -0.0066 0.5665 1.0000
7.750 0.6299 0.05015 0.03969 -0.0034 0.5542 1.0000
8.000 0.6567 0.04931 0.03897 -0.0024 0.5482 1.0000
8.250 0.6633 0.04968 0.03943 -0.0001 0.5357 1.0000
8.500 0.6724 0.05014 0.04002 0.0017 0.5231 1.0000
8.750 0.7068 0.04887 0.03890 0.0021 0.5174 1.0000
9.000 0.7192 0.04927 0.03943 0.0034 0.5041 1.0000
9.250 0.7336 0.04967 0.03995 0.0045 0.4910 1.0000
9.500 0.7535 0.04967 0.04012 0.0052 0.4787 1.0000
9.750 0.7927 0.04795 0.03859 0.0053 0.4710 1.0000
10.000 0.8112 0.04812 0.03891 0.0061 0.4566 1.0000
10.250 0.8325 0.04806 0.03901 0.0068 0.4420 1.0000
10.500 0.8560 0.04783 0.03891 0.0074 0.4270 1.0000
10.750 0.8810 0.04747 0.03868 0.0080 0.4109 1.0000
11.000 0.9071 0.04705 0.03837 0.0085 0.3935 1.0000
11.250 0.9277 0.04717 0.03855 0.0092 0.3743 1.0000
11.500 0.9403 0.04811 0.03958 0.0100 0.3541 1.0000
11.750 0.9560 0.04877 0.04029 0.0107 0.3337 1.0000
12.000 0.9731 0.04932 0.04084 0.0114 0.3133 1.0000
12.250 0.9799 0.05096 0.04253 0.0121 0.2932 1.0000
12.500 0.9876 0.05255 0.04416 0.0128 0.2736 1.0000
12.750 0.9956 0.05416 0.04577 0.0134 0.2547 1.0000
13.000 1.0026 0.05590 0.04748 0.0139 0.2368 1.0000
13.250 1.0074 0.05797 0.04957 0.0143 0.2197 1.0000
13.500 1.0106 0.06032 0.05196 0.0146 0.2035 1.0000
13.750 1.0136 0.06276 0.05443 0.0148 0.1882 1.0000
14.000 1.0167 0.06527 0.05696 0.0148 0.1742 1.0000
14.250 1.0188 0.06792 0.05962 0.0148 0.1608 1.0000
14.500 1.0199 0.07085 0.06263 0.0146 0.1484 1.0000
14.750 1.0195 0.07408 0.06596 0.0142 0.1365 1.0000
15.000 1.0186 0.07743 0.06940 0.0137 0.1256 1.0000
15.250 1.0169 0.08090 0.07292 0.0130 0.1154 1.0000
15.500 1.0154 0.08430 0.07624 0.0121 0.1061 1.0000
15.750 1.0100 0.08868 0.08085 0.0108 0.0971 1.0000
16.000 1.0065 0.09276 0.08500 0.0094 0.0893 1.0000
16.250 1.0040 0.09666 0.08892 0.0080 0.0823 1.0000
16.500 0.9989 0.10139 0.09384 0.0062 0.0761 1.0000
16.750 0.9979 0.10520 0.09763 0.0046 0.0705 1.0000
17.000 0.9924 0.11030 0.10296 0.0024 0.0660 1.0000
17.250 0.9883 0.11505 0.10786 0.0002 0.0619 1.0000
17.500 0.9905 0.11853 0.11130 -0.0013 0.0585 1.0000
17.750 0.9781 0.12546 0.11857 -0.0049 0.0563 1.0000
18.000 0.9654 0.13266 0.12602 -0.0088 0.0544 1.0000
18.250 0.9512 0.14044 0.13401 -0.0132 0.0531 1.0000
18.500 0.9280 0.15100 0.14476 -0.0194 0.0527 1.0000
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