GOE 604 AIRFOIL (goe604-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: GOE 604 AIRFOIL (goe604-il) Reynolds number: 200,000 Max Cl/Cd: 59.23 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe604-il-200000.txt Download as CSV file: xf-goe604-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 604 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.5191 0.05571 0.05198 -0.0868 0.9899 0.0548
-11.000 -0.5364 0.04900 0.04488 -0.0931 0.9733 0.0546
-10.750 -0.5439 0.04318 0.03843 -0.0968 0.9578 0.0550
-10.500 -0.5238 0.03898 0.03398 -0.0998 0.9491 0.0560
-10.250 -0.4854 0.03747 0.03257 -0.1025 0.9397 0.0575
-10.000 -0.4669 0.03464 0.02941 -0.1034 0.9244 0.0583
-9.750 -0.4485 0.03221 0.02663 -0.1035 0.9067 0.0594
-9.500 -0.4309 0.03018 0.02418 -0.1029 0.8865 0.0607
-9.250 -0.4150 0.02867 0.02216 -0.1013 0.8643 0.0619
-9.000 -0.3957 0.02678 0.02009 -0.1003 0.8404 0.0630
-8.750 -0.3734 0.02559 0.01876 -0.0994 0.8175 0.0643
-8.500 -0.3516 0.02469 0.01767 -0.0983 0.7961 0.0659
-8.250 -0.3308 0.02384 0.01654 -0.0970 0.7764 0.0676
-8.000 -0.3103 0.02311 0.01547 -0.0955 0.7586 0.0692
-7.750 -0.2882 0.02200 0.01420 -0.0945 0.7428 0.0708
-7.500 -0.2647 0.02122 0.01336 -0.0937 0.7288 0.0726
-7.250 -0.2413 0.02065 0.01265 -0.0927 0.7165 0.0750
-7.000 -0.2182 0.02013 0.01194 -0.0917 0.7041 0.0775
-6.750 -0.1950 0.01935 0.01110 -0.0908 0.6934 0.0800
-6.500 -0.1715 0.01882 0.01053 -0.0899 0.6834 0.0830
-6.250 -0.1480 0.01839 0.01000 -0.0889 0.6735 0.0866
-6.000 -0.1253 0.01783 0.00941 -0.0879 0.6646 0.0910
-5.750 -0.1018 0.01747 0.00902 -0.0869 0.6557 0.0966
-5.500 -0.0789 0.01704 0.00859 -0.0859 0.6474 0.1033
-5.250 -0.0551 0.01675 0.00829 -0.0850 0.6398 0.1136
-5.000 -0.0311 0.01651 0.00810 -0.0841 0.6319 0.1297
-4.750 -0.0063 0.01633 0.00788 -0.0833 0.6253 0.1543
-4.500 0.0174 0.01619 0.00779 -0.0824 0.6178 0.1778
-4.250 0.0423 0.01611 0.00766 -0.0817 0.6108 0.1959
-4.000 0.0679 0.01607 0.00757 -0.0812 0.6047 0.2107
-3.750 0.0925 0.01598 0.00750 -0.0804 0.5976 0.2237
-3.500 0.1186 0.01596 0.00738 -0.0799 0.5914 0.2363
-3.250 0.1444 0.01593 0.00733 -0.0794 0.5854 0.2488
-3.000 0.1690 0.01581 0.00726 -0.0787 0.5785 0.2610
-2.750 0.1951 0.01574 0.00714 -0.0781 0.5724 0.2749
-2.500 0.2209 0.01574 0.00710 -0.0776 0.5667 0.2914
-2.250 0.2451 0.01563 0.00709 -0.0768 0.5601 0.3111
-2.000 0.2702 0.01549 0.00700 -0.0761 0.5544 0.3336
-1.750 0.2954 0.01539 0.00695 -0.0755 0.5492 0.3606
-1.500 0.3182 0.01519 0.00692 -0.0745 0.5425 0.3930
-1.250 0.3418 0.01498 0.00683 -0.0735 0.5366 0.4335
-1.000 0.3654 0.01482 0.00680 -0.0726 0.5314 0.4867
-0.750 0.3844 0.01452 0.00687 -0.0707 0.5249 0.5610
-0.500 0.4035 0.01416 0.00693 -0.0686 0.5193 0.6737
-0.250 0.4355 0.01399 0.00710 -0.0684 0.5143 0.8182
0.000 0.4954 0.01417 0.00741 -0.0741 0.5062 0.9062
0.250 0.5491 0.01440 0.00749 -0.0787 0.4996 0.9410
0.500 0.5979 0.01469 0.00765 -0.0826 0.4932 0.9629
0.750 0.6487 0.01488 0.00775 -0.0871 0.4858 0.9794
1.000 0.7063 0.01503 0.00768 -0.0930 0.4795 0.9919
1.250 0.7532 0.01513 0.00775 -0.0971 0.4725 1.0000
1.500 0.7718 0.01525 0.00780 -0.0956 0.4673 1.0000
1.750 0.7923 0.01539 0.00782 -0.0943 0.4630 1.0000
2.000 0.8121 0.01561 0.00798 -0.0929 0.4585 1.0000
2.250 0.8301 0.01579 0.00817 -0.0912 0.4534 1.0000
2.500 0.8503 0.01597 0.00828 -0.0899 0.4490 1.0000
2.750 0.8724 0.01617 0.00837 -0.0889 0.4452 1.0000
3.000 0.8927 0.01645 0.00861 -0.0876 0.4412 1.0000
3.250 0.9110 0.01668 0.00886 -0.0859 0.4365 1.0000
3.500 0.9316 0.01686 0.00899 -0.0846 0.4320 1.0000
3.750 0.9544 0.01704 0.00905 -0.0837 0.4280 1.0000
4.000 0.9741 0.01731 0.00932 -0.0823 0.4236 1.0000
4.250 0.9926 0.01756 0.00959 -0.0806 0.4193 1.0000
4.500 1.0137 0.01778 0.00977 -0.0794 0.4153 1.0000
4.750 1.0367 0.01800 0.00992 -0.0786 0.4119 1.0000
5.000 1.0604 0.01834 0.01018 -0.0780 0.4086 1.0000
5.250 1.0772 0.01865 0.01057 -0.0761 0.4049 1.0000
5.500 1.0968 0.01894 0.01089 -0.0747 0.4013 1.0000
5.750 1.1186 0.01920 0.01113 -0.0737 0.3981 1.0000
6.000 1.1424 0.01947 0.01133 -0.0731 0.3951 1.0000
6.250 1.1673 0.01986 0.01166 -0.0727 0.3921 1.0000
6.500 1.1816 0.02020 0.01211 -0.0705 0.3885 1.0000
6.750 1.1995 0.02050 0.01246 -0.0689 0.3849 1.0000
7.000 1.2205 0.02075 0.01269 -0.0678 0.3814 1.0000
7.250 1.2444 0.02102 0.01291 -0.0673 0.3785 1.0000
7.500 1.2711 0.02146 0.01328 -0.0673 0.3758 1.0000
7.750 1.2834 0.02188 0.01384 -0.0649 0.3729 1.0000
8.000 1.2982 0.02225 0.01430 -0.0629 0.3693 1.0000
8.250 1.3168 0.02253 0.01460 -0.0615 0.3659 1.0000
8.500 1.3395 0.02282 0.01485 -0.0608 0.3629 1.0000
8.750 1.3674 0.02320 0.01516 -0.0611 0.3601 1.0000
9.000 1.3787 0.02371 0.01580 -0.0587 0.3572 1.0000
9.250 1.3888 0.02419 0.01639 -0.0561 0.3540 1.0000
9.500 1.4030 0.02456 0.01683 -0.0541 0.3506 1.0000
9.750 1.4225 0.02484 0.01710 -0.0530 0.3473 1.0000
10.000 1.4508 0.02513 0.01730 -0.0534 0.3440 1.0000
10.250 1.4542 0.02569 0.01798 -0.0497 0.3408 1.0000
10.500 1.4543 0.02625 0.01867 -0.0456 0.3374 1.0000
10.750 1.4637 0.02669 0.01918 -0.0432 0.3338 1.0000
11.000 1.4826 0.02698 0.01944 -0.0421 0.3303 1.0000
11.250 1.5095 0.02733 0.01973 -0.0424 0.3266 1.0000
11.500 1.4989 0.02826 0.02087 -0.0375 0.3231 1.0000
11.750 1.5001 0.02905 0.02177 -0.0345 0.3190 1.0000
12.000 1.5136 0.02949 0.02221 -0.0330 0.3149 1.0000
12.250 1.5411 0.02970 0.02232 -0.0333 0.3107 1.0000
12.500 1.5225 0.03129 0.02415 -0.0287 0.3064 1.0000
12.750 1.5223 0.03240 0.02535 -0.0263 0.3015 1.0000
13.000 1.5396 0.03278 0.02567 -0.0255 0.2969 1.0000
13.250 1.5327 0.03446 0.02749 -0.0231 0.2917 1.0000
13.500 1.5246 0.03632 0.02947 -0.0209 0.2859 1.0000
13.750 1.5417 0.03678 0.02985 -0.0203 0.2808 1.0000
14.000 1.5232 0.03970 0.03296 -0.0183 0.2746 1.0000
14.250 1.5200 0.04169 0.03499 -0.0172 0.2684 1.0000
14.500 1.5289 0.04289 0.03615 -0.0165 0.2630 1.0000
14.750 1.5077 0.04673 0.04016 -0.0155 0.2564 1.0000
15.000 1.5173 0.04794 0.04132 -0.0151 0.2513 1.0000
15.250 1.5043 0.05145 0.04494 -0.0147 0.2455 1.0000
15.500 1.4967 0.05458 0.04815 -0.0145 0.2403 1.0000
15.750 1.5131 0.05518 0.04866 -0.0142 0.2359 1.0000
16.000 1.4953 0.05962 0.05326 -0.0143 0.2313 1.0000
16.250 1.4865 0.06316 0.05689 -0.0145 0.2269 1.0000
16.500 1.4964 0.06456 0.05827 -0.0144 0.2233 1.0000
16.750 1.5043 0.06623 0.05994 -0.0143 0.2200 1.0000
17.000 1.4831 0.07151 0.06541 -0.0149 0.2166 1.0000
17.250 1.4749 0.07527 0.06927 -0.0155 0.2132 1.0000
17.500 1.4826 0.07703 0.07105 -0.0156 0.2104 1.0000
17.750 1.5151 0.07561 0.06951 -0.0149 0.2075 1.0000
18.000 1.4830 0.08255 0.07669 -0.0163 0.2050 1.0000
18.250 1.4473 0.09024 0.08460 -0.0180 0.2023 1.0000
18.500 1.4243 0.09636 0.09086 -0.0195 0.1993 1.0000
|
Polar data table (+)
Polar graphs
<< Back to GOE 604 AIRFOIL (goe604-il)