GOE 199 (L.F.G. 5406) AIRFOIL (goe199-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: GOE 199 (L.F.G. 5406) AIRFOIL (goe199-il) Reynolds number: 100,000 Max Cl/Cd: 54.88 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe199-il-100000-n5.txt Download as CSV file: xf-goe199-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 199 (L.F.G. 5406) 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
------ -------- --------- --------- -------- -------- --------
-7.250 -0.3089 0.09301 0.08850 -0.0250 1.0000 0.0340
-7.000 -0.3083 0.09068 0.08624 -0.0250 1.0000 0.0346
-6.750 -0.3100 0.08863 0.08427 -0.0245 1.0000 0.0353
-6.500 -0.3138 0.08683 0.08254 -0.0236 1.0000 0.0359
-6.250 -0.2937 0.08315 0.07882 -0.0288 0.9949 0.0375
-6.000 -0.2407 0.07937 0.07481 -0.0462 0.9860 0.0401
-5.750 -0.2251 0.07407 0.06955 -0.0472 0.9804 0.0411
-5.500 -0.2019 0.06997 0.06544 -0.0495 0.9753 0.0434
-5.250 -0.1683 0.06596 0.06133 -0.0557 0.9677 0.0463
-5.000 -0.1043 0.06202 0.05696 -0.0703 0.9610 0.0503
-4.750 -0.0911 0.05757 0.05262 -0.0697 0.9529 0.0521
-4.500 -0.0375 0.05533 0.04994 -0.0785 0.9468 0.0606
-4.250 -0.0161 0.05087 0.04551 -0.0801 0.9388 0.0619
-4.000 0.0107 0.04761 0.04223 -0.0822 0.9333 0.0649
-3.750 0.0564 0.04572 0.03982 -0.0874 0.9249 0.0727
-3.500 0.0775 0.04206 0.03629 -0.0883 0.9187 0.0762
-3.250 0.1153 0.04019 0.03402 -0.0913 0.9103 0.0859
-3.000 0.1415 0.03732 0.03115 -0.0925 0.9036 0.0894
-2.750 0.1757 0.03566 0.02912 -0.0944 0.8951 0.1003
-2.500 0.2032 0.03331 0.02674 -0.0953 0.8880 0.1049
-2.250 0.2312 0.03169 0.02497 -0.0961 0.8790 0.1205
-2.000 0.2608 0.03026 0.02336 -0.0971 0.8718 0.1476
-1.750 0.3069 0.02711 0.01920 -0.0968 0.8631 0.0618
-1.500 0.3360 0.02552 0.01745 -0.0969 0.8552 0.0575
-1.250 0.3651 0.02416 0.01582 -0.0968 0.8450 0.0548
-1.000 0.3934 0.02311 0.01451 -0.0964 0.8334 0.0553
-0.750 0.4211 0.02216 0.01330 -0.0957 0.8196 0.0559
-0.500 0.4484 0.02120 0.01206 -0.0947 0.8035 0.0545
-0.250 0.4754 0.02036 0.01097 -0.0938 0.7867 0.0534
0.000 0.5023 0.01964 0.01003 -0.0929 0.7703 0.0526
0.250 0.5292 0.01902 0.00925 -0.0921 0.7542 0.0522
0.500 0.5560 0.01847 0.00859 -0.0915 0.7382 0.0522
0.750 0.5827 0.01799 0.00803 -0.0908 0.7219 0.0525
1.000 0.6092 0.01760 0.00761 -0.0903 0.7047 0.0548
1.250 0.6352 0.01728 0.00722 -0.0896 0.6866 0.0574
1.500 0.6614 0.01700 0.00687 -0.0889 0.6659 0.0585
1.750 0.6881 0.01681 0.00655 -0.0884 0.6436 0.0594
2.000 0.7147 0.01671 0.00630 -0.0878 0.6194 0.0606
2.250 0.7410 0.01664 0.00607 -0.0873 0.5935 0.0627
2.500 0.7672 0.01668 0.00593 -0.0867 0.5670 0.0661
2.750 0.7932 0.01681 0.00589 -0.0862 0.5415 0.0727
3.250 0.8447 0.01556 0.00601 -0.0854 0.4916 1.0000
3.500 0.8699 0.01592 0.00617 -0.0849 0.4650 1.0000
3.750 0.8948 0.01632 0.00636 -0.0844 0.4373 1.0000
4.000 0.9193 0.01675 0.00659 -0.0838 0.4091 1.0000
4.250 0.9437 0.01721 0.00689 -0.0833 0.3828 1.0000
4.500 0.9678 0.01770 0.00721 -0.0828 0.3607 1.0000
4.750 0.9920 0.01820 0.00758 -0.0823 0.3427 1.0000
5.000 1.0161 0.01871 0.00799 -0.0818 0.3283 1.0000
5.250 1.0402 0.01924 0.00845 -0.0813 0.3166 1.0000
5.500 1.0644 0.01975 0.00893 -0.0808 0.3065 1.0000
5.750 1.0887 0.02027 0.00944 -0.0804 0.2984 1.0000
6.000 1.1129 0.02081 0.01000 -0.0799 0.2914 1.0000
6.250 1.1370 0.02138 0.01055 -0.0794 0.2857 1.0000
6.500 1.1615 0.02191 0.01116 -0.0790 0.2801 1.0000
6.750 1.1856 0.02249 0.01177 -0.0786 0.2755 1.0000
7.000 1.2098 0.02311 0.01243 -0.0782 0.2715 1.0000
7.250 1.2344 0.02368 0.01314 -0.0778 0.2673 1.0000
7.500 1.2586 0.02427 0.01384 -0.0774 0.2632 1.0000
7.750 1.2819 0.02490 0.01452 -0.0769 0.2581 1.0000
8.000 1.3043 0.02542 0.01523 -0.0763 0.2505 1.0000
8.250 1.3254 0.02599 0.01581 -0.0755 0.2425 1.0000
8.500 1.3464 0.02647 0.01655 -0.0746 0.2338 1.0000
8.750 1.3656 0.02698 0.01722 -0.0736 0.2236 1.0000
9.000 1.3831 0.02750 0.01785 -0.0723 0.2114 1.0000
9.250 1.3998 0.02802 0.01854 -0.0709 0.1962 1.0000
9.500 1.4158 0.02857 0.01928 -0.0694 0.1732 1.0000
9.750 1.4260 0.02966 0.02019 -0.0674 0.0970 1.0000
10.000 1.4208 0.03250 0.02256 -0.0638 0.0603 1.0000
10.250 1.4202 0.03474 0.02481 -0.0605 0.0471 1.0000
10.500 1.4194 0.03672 0.02690 -0.0572 0.0415 1.0000
10.750 1.4148 0.03908 0.02938 -0.0540 0.0383 1.0000
11.000 1.4118 0.04142 0.03193 -0.0514 0.0361 1.0000
11.250 1.4076 0.04402 0.03475 -0.0492 0.0341 1.0000
11.500 1.4009 0.04703 0.03796 -0.0476 0.0324 1.0000
11.750 1.3914 0.05057 0.04169 -0.0464 0.0310 1.0000
12.000 1.3787 0.05474 0.04603 -0.0458 0.0301 1.0000
12.250 1.3638 0.05950 0.05097 -0.0458 0.0293 1.0000
12.500 1.3504 0.06441 0.05605 -0.0463 0.0288 1.0000
12.750 1.3398 0.06925 0.06109 -0.0472 0.0283 1.0000
13.000 1.3287 0.07435 0.06638 -0.0483 0.0278 1.0000
13.250 1.3182 0.07948 0.07168 -0.0495 0.0273 1.0000
13.500 1.3095 0.08437 0.07672 -0.0506 0.0268 1.0000
13.750 1.3030 0.08888 0.08139 -0.0515 0.0261 1.0000
14.000 1.2985 0.09303 0.08567 -0.0522 0.0253 1.0000
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Polar data table (+)
Polar graphs
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