GOE 681 AIRFOIL (goe681-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 681 AIRFOIL (goe681-il) Reynolds number: 100,000 Max Cl/Cd: 42.15 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe681-il-100000-n5.txt Download as CSV file: xf-goe681-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 681 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
------ -------- --------- --------- -------- -------- --------
-11.000 -0.5377 0.05743 0.05136 -0.0875 0.9854 0.0507
-10.750 -0.5643 0.05012 0.04358 -0.0956 0.9695 0.0507
-10.500 -0.5738 0.04614 0.03920 -0.0971 0.9554 0.0510
-10.250 -0.5709 0.04313 0.03586 -0.0976 0.9431 0.0515
-10.000 -0.5496 0.04136 0.03402 -0.0987 0.9363 0.0521
-9.750 -0.5330 0.03955 0.03206 -0.0990 0.9272 0.0526
-9.500 -0.5078 0.03760 0.02990 -0.1007 0.9222 0.0532
-9.250 -0.4946 0.03607 0.02820 -0.0996 0.9114 0.0538
-9.000 -0.4694 0.03432 0.02623 -0.1006 0.9057 0.0544
-8.750 -0.4522 0.03295 0.02466 -0.0997 0.8965 0.0552
-8.250 -0.4000 0.03017 0.02143 -0.1006 0.8844 0.0568
-8.000 -0.3817 0.02937 0.02065 -0.0994 0.8747 0.0575
-7.750 -0.3535 0.02842 0.01963 -0.0999 0.8690 0.0587
-7.500 -0.3307 0.02763 0.01875 -0.0993 0.8615 0.0601
-7.250 -0.3083 0.02685 0.01785 -0.0986 0.8535 0.0619
-7.000 -0.2796 0.02601 0.01693 -0.0990 0.8482 0.0638
-6.750 -0.2602 0.02545 0.01633 -0.0977 0.8396 0.0656
-6.500 -0.2362 0.02478 0.01556 -0.0971 0.8324 0.0680
-6.250 -0.2075 0.02402 0.01473 -0.0973 0.8272 0.0707
-6.000 -0.1903 0.02356 0.01425 -0.0955 0.8183 0.0737
-5.750 -0.1660 0.02295 0.01357 -0.0948 0.8114 0.0780
-5.500 -0.1372 0.02227 0.01283 -0.0950 0.8064 0.0853
-5.250 -0.1208 0.02188 0.01245 -0.0930 0.7974 0.0935
-5.000 -0.0966 0.02131 0.01195 -0.0924 0.7907 0.1061
-4.750 -0.0672 0.02080 0.01148 -0.0926 0.7858 0.1245
-4.500 -0.0498 0.02067 0.01143 -0.0907 0.7769 0.1404
-4.250 -0.0233 0.02050 0.01128 -0.0902 0.7704 0.1591
-4.000 0.0081 0.02036 0.01102 -0.0906 0.7654 0.1798
-3.750 0.0264 0.02044 0.01110 -0.0888 0.7565 0.1956
-3.500 0.0525 0.02040 0.01101 -0.0883 0.7499 0.2128
-3.250 0.0811 0.02026 0.01084 -0.0881 0.7440 0.2285
-3.000 0.1005 0.02020 0.01075 -0.0864 0.7336 0.2405
-2.750 0.1312 0.01990 0.01036 -0.0864 0.7256 0.2532
-2.500 0.1506 0.01975 0.01019 -0.0845 0.7136 0.2619
-2.250 0.1808 0.01943 0.00979 -0.0845 0.7054 0.2720
-2.000 0.2005 0.01936 0.00970 -0.0828 0.6950 0.2808
-1.750 0.2280 0.01911 0.00945 -0.0824 0.6877 0.2925
-1.500 0.2500 0.01901 0.00937 -0.0811 0.6786 0.3044
-1.250 0.2755 0.01883 0.00918 -0.0804 0.6704 0.3176
-1.000 0.2999 0.01865 0.00904 -0.0795 0.6620 0.3290
-0.750 0.3237 0.01852 0.00890 -0.0784 0.6527 0.3420
-0.500 0.3492 0.01832 0.00875 -0.0777 0.6443 0.3570
-0.250 0.3714 0.01819 0.00869 -0.0764 0.6343 0.3756
0.000 0.3968 0.01799 0.00855 -0.0756 0.6253 0.4042
0.250 0.4184 0.01782 0.00854 -0.0743 0.6148 0.4465
0.500 0.4423 0.01754 0.00847 -0.0732 0.6050 0.5129
0.750 0.4624 0.01718 0.00850 -0.0713 0.5942 0.6127
1.000 0.5019 0.01686 0.00874 -0.0725 0.5819 0.8029
1.250 0.5721 0.01694 0.00882 -0.0801 0.5670 0.9124
1.500 0.6211 0.01708 0.00880 -0.0839 0.5526 0.9535
1.750 0.6624 0.01727 0.00887 -0.0865 0.5369 0.9806
2.000 0.7071 0.01746 0.00891 -0.0900 0.5201 1.0000
2.250 0.7215 0.01763 0.00895 -0.0874 0.5063 1.0000
2.500 0.7360 0.01781 0.00899 -0.0849 0.4924 1.0000
2.750 0.7503 0.01801 0.00904 -0.0823 0.4781 1.0000
3.000 0.7639 0.01825 0.00917 -0.0796 0.4636 1.0000
3.250 0.7778 0.01851 0.00931 -0.0770 0.4498 1.0000
3.500 0.7915 0.01880 0.00945 -0.0744 0.4365 1.0000
3.750 0.8051 0.01910 0.00961 -0.0717 0.4239 1.0000
4.000 0.8184 0.01943 0.00984 -0.0691 0.4114 1.0000
4.250 0.8320 0.01978 0.01006 -0.0665 0.4005 1.0000
4.500 0.8455 0.02015 0.01030 -0.0639 0.3902 1.0000
4.750 0.8598 0.02053 0.01059 -0.0615 0.3812 1.0000
5.000 0.8735 0.02092 0.01087 -0.0590 0.3732 1.0000
5.250 0.8880 0.02131 0.01118 -0.0567 0.3661 1.0000
5.500 0.9027 0.02172 0.01153 -0.0544 0.3591 1.0000
5.750 0.9184 0.02215 0.01184 -0.0524 0.3530 1.0000
6.000 0.9346 0.02260 0.01224 -0.0505 0.3469 1.0000
6.250 0.9506 0.02305 0.01266 -0.0487 0.3409 1.0000
6.500 0.9681 0.02352 0.01304 -0.0471 0.3357 1.0000
6.750 0.9864 0.02401 0.01347 -0.0456 0.3309 1.0000
7.000 1.0033 0.02451 0.01398 -0.0440 0.3259 1.0000
7.250 1.0213 0.02502 0.01446 -0.0427 0.3215 1.0000
7.500 1.0417 0.02553 0.01490 -0.0416 0.3177 1.0000
7.750 1.0631 0.02606 0.01537 -0.0408 0.3141 1.0000
8.000 1.0792 0.02664 0.01602 -0.0393 0.3102 1.0000
8.250 1.0965 0.02722 0.01662 -0.0379 0.3062 1.0000
8.500 1.1147 0.02780 0.01719 -0.0367 0.3025 1.0000
8.750 1.1362 0.02835 0.01768 -0.0360 0.2993 1.0000
9.000 1.1576 0.02897 0.01827 -0.0353 0.2963 1.0000
9.250 1.1720 0.02968 0.01909 -0.0337 0.2933 1.0000
9.500 1.1880 0.03040 0.01988 -0.0324 0.2903 1.0000
9.750 1.2049 0.03111 0.02063 -0.0313 0.2875 1.0000
10.000 1.2233 0.03179 0.02134 -0.0303 0.2848 1.0000
10.250 1.2439 0.03243 0.02195 -0.0296 0.2822 1.0000
10.500 1.2688 0.03305 0.02252 -0.0295 0.2796 1.0000
10.750 1.2760 0.03405 0.02369 -0.0273 0.2772 1.0000
11.000 1.2853 0.03507 0.02484 -0.0255 0.2746 1.0000
11.250 1.2968 0.03608 0.02596 -0.0241 0.2722 1.0000
11.500 1.3092 0.03706 0.02703 -0.0227 0.2699 1.0000
11.750 1.3234 0.03799 0.02801 -0.0216 0.2677 1.0000
12.000 1.3411 0.03879 0.02884 -0.0208 0.2654 1.0000
12.250 1.3637 0.03946 0.02950 -0.0205 0.2634 1.0000
12.500 1.3716 0.04074 0.03088 -0.0190 0.2613 1.0000
12.750 1.3665 0.04257 0.03293 -0.0166 0.2591 1.0000
13.000 1.3627 0.04450 0.03506 -0.0145 0.2568 1.0000
13.250 1.3599 0.04643 0.03714 -0.0127 0.2543 1.0000
13.500 1.3627 0.04808 0.03889 -0.0113 0.2517 1.0000
13.750 1.3755 0.04908 0.03992 -0.0105 0.2490 1.0000
14.000 1.4047 0.04904 0.03980 -0.0105 0.2462 1.0000
14.250 1.3867 0.05219 0.04318 -0.0085 0.2439 1.0000
14.500 1.3515 0.05700 0.04829 -0.0066 0.2414 1.0000
14.750 1.3071 0.06339 0.05495 -0.0057 0.2385 1.0000
15.000 1.1915 0.07952 0.07148 -0.0078 0.2340 1.0000
15.250 1.2965 0.06923 0.06098 -0.0051 0.2323 1.0000
15.500 1.3647 0.06441 0.05595 -0.0043 0.2293 1.0000
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