GOE 407 AIRFOIL (goe407-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 407 AIRFOIL (goe407-il) Reynolds number: 100,000 Max Cl/Cd: 57.72 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe407-il-100000-n5.txt Download as CSV file: xf-goe407-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 407 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3322 0.10521 0.10037 -0.0335 1.0000 0.0556
-8.250 -0.3475 0.10391 0.09918 -0.0330 1.0000 0.0557
-8.000 -0.3614 0.10243 0.09779 -0.0321 1.0000 0.0557
-7.750 -0.3363 0.09689 0.09225 -0.0289 1.0000 0.0567
-7.500 -0.3406 0.09482 0.09025 -0.0266 1.0000 0.0574
-7.250 -0.3313 0.09183 0.08729 -0.0280 0.9964 0.0588
-7.000 -0.3099 0.08787 0.08330 -0.0344 0.9880 0.0622
-6.750 -0.2803 0.08334 0.07857 -0.0529 0.9721 0.0649
-6.500 -0.2648 0.07863 0.07391 -0.0532 0.9648 0.0656
-6.250 -0.2436 0.07470 0.06998 -0.0541 0.9600 0.0667
-6.000 -0.2259 0.07138 0.06664 -0.0559 0.9494 0.0682
-5.750 -0.2061 0.06801 0.06321 -0.0589 0.9382 0.0701
-5.500 -0.1784 0.06476 0.05968 -0.0663 0.9240 0.0750
-5.250 -0.1545 0.06050 0.05527 -0.0700 0.9154 0.0764
-5.000 -0.1398 0.05741 0.05224 -0.0692 0.9045 0.0778
-4.750 -0.1193 0.05458 0.04933 -0.0700 0.8948 0.0797
-4.500 -0.0922 0.05149 0.04610 -0.0724 0.8873 0.0820
-4.250 -0.0601 0.04980 0.04380 -0.0756 0.8756 0.0878
-3.500 0.0215 0.03670 0.02974 -0.0783 0.8535 0.0555
-3.250 0.0489 0.03441 0.02732 -0.0790 0.8457 0.0548
-3.000 0.0784 0.03219 0.02486 -0.0798 0.8389 0.0535
-2.750 0.1065 0.03004 0.02240 -0.0800 0.8308 0.0523
-2.500 0.1378 0.02792 0.01990 -0.0806 0.8242 0.0512
-2.250 0.1659 0.02613 0.01772 -0.0803 0.8152 0.0505
-2.000 0.1972 0.02455 0.01577 -0.0807 0.8063 0.0503
-1.750 0.2290 0.02341 0.01433 -0.0811 0.7961 0.0518
-1.500 0.2568 0.02243 0.01306 -0.0807 0.7846 0.0530
-1.250 0.2882 0.02140 0.01175 -0.0810 0.7750 0.0534
-1.000 0.3168 0.02055 0.01068 -0.0808 0.7648 0.0537
-0.750 0.3450 0.01984 0.00979 -0.0805 0.7550 0.0541
-0.500 0.3758 0.01915 0.00895 -0.0807 0.7461 0.0549
-0.250 0.4013 0.01868 0.00838 -0.0800 0.7359 0.0557
0.000 0.4301 0.01817 0.00788 -0.0800 0.7273 0.0571
0.250 0.4550 0.01790 0.00762 -0.0793 0.7171 0.0606
0.500 0.4813 0.01762 0.00727 -0.0787 0.7076 0.0641
0.750 0.5083 0.01730 0.00692 -0.0783 0.6983 0.0670
1.000 0.5355 0.01711 0.00669 -0.0780 0.6880 0.0714
1.250 0.5668 0.01690 0.00639 -0.0784 0.6785 0.0794
1.500 0.5961 0.01668 0.00623 -0.0786 0.6678 0.1041
2.000 0.7575 0.01500 0.00625 -0.1016 0.6402 1.0000
2.250 0.7812 0.01516 0.00629 -0.1006 0.6292 1.0000
2.500 0.8039 0.01533 0.00636 -0.0993 0.6172 1.0000
2.750 0.8258 0.01552 0.00649 -0.0980 0.6046 1.0000
3.000 0.8478 0.01570 0.00662 -0.0967 0.5917 1.0000
3.250 0.8697 0.01590 0.00674 -0.0953 0.5785 1.0000
3.500 0.8911 0.01609 0.00688 -0.0939 0.5644 1.0000
3.750 0.9121 0.01629 0.00704 -0.0924 0.5496 1.0000
4.000 0.9325 0.01650 0.00724 -0.0908 0.5342 1.0000
4.250 0.9528 0.01673 0.00742 -0.0892 0.5183 1.0000
4.500 0.9729 0.01697 0.00761 -0.0875 0.5021 1.0000
4.750 0.9927 0.01723 0.00783 -0.0858 0.4856 1.0000
5.000 1.0118 0.01753 0.00804 -0.0840 0.4682 1.0000
5.250 1.0305 0.01787 0.00829 -0.0822 0.4513 1.0000
5.500 1.0491 0.01824 0.00857 -0.0804 0.4358 1.0000
5.750 1.0681 0.01864 0.00891 -0.0787 0.4228 1.0000
6.000 1.0873 0.01905 0.00930 -0.0770 0.4108 1.0000
6.250 1.1066 0.01947 0.00971 -0.0755 0.4002 1.0000
6.500 1.1253 0.01991 0.01013 -0.0738 0.3894 1.0000
6.750 1.1432 0.02036 0.01058 -0.0720 0.3779 1.0000
7.000 1.1614 0.02080 0.01106 -0.0703 0.3676 1.0000
7.250 1.1799 0.02127 0.01151 -0.0686 0.3593 1.0000
7.500 1.1977 0.02171 0.01207 -0.0668 0.3497 1.0000
7.750 1.2142 0.02218 0.01256 -0.0649 0.3397 1.0000
8.000 1.2299 0.02266 0.01308 -0.0628 0.3296 1.0000
8.250 1.2453 0.02314 0.01364 -0.0606 0.3195 1.0000
8.500 1.2601 0.02366 0.01420 -0.0584 0.3105 1.0000
8.750 1.2743 0.02416 0.01483 -0.0562 0.3006 1.0000
9.000 1.2871 0.02470 0.01545 -0.0536 0.2907 1.0000
9.250 1.2969 0.02526 0.01604 -0.0506 0.2807 1.0000
9.500 1.3059 0.02581 0.01672 -0.0475 0.2692 1.0000
9.750 1.3139 0.02642 0.01744 -0.0443 0.2578 1.0000
10.000 1.3207 0.02711 0.01818 -0.0411 0.2458 1.0000
10.250 1.3261 0.02790 0.01902 -0.0378 0.2323 1.0000
10.500 1.3303 0.02880 0.01997 -0.0346 0.2169 1.0000
10.750 1.3338 0.02984 0.02105 -0.0315 0.1996 1.0000
11.000 1.3360 0.03104 0.02226 -0.0285 0.1817 1.0000
11.250 1.3365 0.03244 0.02365 -0.0256 0.1655 1.0000
11.500 1.3358 0.03405 0.02522 -0.0229 0.1523 1.0000
11.750 1.3341 0.03585 0.02699 -0.0204 0.1418 1.0000
12.000 1.3304 0.03794 0.02904 -0.0182 0.1334 1.0000
12.250 1.3309 0.03987 0.03105 -0.0164 0.1264 1.0000
12.500 1.3259 0.04232 0.03349 -0.0146 0.1197 1.0000
12.750 1.3264 0.04446 0.03576 -0.0133 0.1136 1.0000
13.000 1.3219 0.04712 0.03850 -0.0121 0.1071 1.0000
13.250 1.3192 0.04973 0.04120 -0.0111 0.1016 1.0000
13.500 1.3185 0.05225 0.04390 -0.0104 0.0962 1.0000
13.750 1.3113 0.05555 0.04725 -0.0099 0.0910 1.0000
14.000 1.3103 0.05833 0.05025 -0.0096 0.0848 1.0000
14.250 1.3042 0.06181 0.05384 -0.0096 0.0795 1.0000
14.500 1.2984 0.06540 0.05759 -0.0098 0.0725 1.0000
14.750 1.2886 0.06964 0.06193 -0.0103 0.0672 1.0000
15.000 1.2802 0.07389 0.06632 -0.0110 0.0608 1.0000
15.250 1.2679 0.07883 0.07132 -0.0121 0.0566 1.0000
15.500 1.2569 0.08376 0.07636 -0.0133 0.0514 1.0000
15.750 1.2435 0.08923 0.08191 -0.0149 0.0478 1.0000
16.000 1.2326 0.09439 0.08715 -0.0164 0.0446 1.0000
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Polar data table (+)
Polar graphs
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