GOE 681 AIRFOIL (goe681-il) Xfoil prediction polar at RE=200,000 Ncrit=9
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Airfoil: GOE 681 AIRFOIL (goe681-il) Reynolds number: 200,000 Max Cl/Cd: 61.69 at α=2.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe681-il-200000.txt Download as CSV file: xf-goe681-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.5928 0.05006 0.04527 -0.0971 0.9702 0.0584
-10.500 -0.5881 0.04600 0.04092 -0.0988 0.9601 0.0580
-10.250 -0.5757 0.04192 0.03647 -0.1013 0.9543 0.0579
-10.000 -0.5682 0.03907 0.03330 -0.1010 0.9440 0.0579
-9.750 -0.5479 0.03611 0.02987 -0.1026 0.9393 0.0582
-9.500 -0.5296 0.03381 0.02739 -0.1025 0.9315 0.0586
-9.250 -0.5013 0.03174 0.02516 -0.1039 0.9265 0.0590
-9.000 -0.4678 0.02980 0.02303 -0.1059 0.9231 0.0594
-8.750 -0.4410 0.02836 0.02145 -0.1064 0.9169 0.0599
-8.500 -0.4152 0.02710 0.02005 -0.1065 0.9096 0.0605
-8.250 -0.3813 0.02572 0.01853 -0.1080 0.9054 0.0612
-8.000 -0.3554 0.02467 0.01733 -0.1078 0.8982 0.0620
-7.750 -0.3293 0.02368 0.01620 -0.1075 0.8907 0.0629
-7.500 -0.2960 0.02267 0.01499 -0.1085 0.8859 0.0641
-7.250 -0.2749 0.02189 0.01419 -0.1073 0.8769 0.0653
-7.000 -0.2462 0.02112 0.01345 -0.1075 0.8701 0.0669
-6.750 -0.2153 0.02040 0.01267 -0.1080 0.8646 0.0689
-6.500 -0.1963 0.01994 0.01214 -0.1061 0.8550 0.0705
-6.250 -0.1681 0.01918 0.01136 -0.1061 0.8486 0.0726
-6.000 -0.1463 0.01870 0.01091 -0.1049 0.8407 0.0750
-5.750 -0.1228 0.01825 0.01040 -0.1038 0.8328 0.0786
-5.500 -0.0959 0.01762 0.00979 -0.1036 0.8271 0.0833
-5.250 -0.0784 0.01721 0.00942 -0.1015 0.8181 0.0899
-5.000 -0.0554 0.01661 0.00888 -0.1005 0.8110 0.1042
-4.750 -0.0308 0.01601 0.00846 -0.0999 0.8052 0.1355
-4.500 -0.0110 0.01595 0.00850 -0.0982 0.7962 0.1618
-4.250 0.0181 0.01593 0.00840 -0.0980 0.7891 0.1839
-4.000 0.0417 0.01596 0.00840 -0.0969 0.7803 0.1989
-3.750 0.0673 0.01586 0.00825 -0.0960 0.7711 0.2120
-3.500 0.0933 0.01580 0.00810 -0.0953 0.7624 0.2254
-3.250 0.1171 0.01575 0.00802 -0.0942 0.7530 0.2376
-3.000 0.1461 0.01559 0.00780 -0.0941 0.7466 0.2494
-2.750 0.1675 0.01560 0.00778 -0.0926 0.7376 0.2598
-2.500 0.1941 0.01538 0.00758 -0.0921 0.7303 0.2711
-2.250 0.2201 0.01537 0.00747 -0.0914 0.7231 0.2824
-2.000 0.2437 0.01514 0.00734 -0.0904 0.7146 0.2931
-1.750 0.2727 0.01503 0.00709 -0.0903 0.7078 0.3031
-1.500 0.2949 0.01481 0.00699 -0.0890 0.6991 0.3121
-1.250 0.3218 0.01467 0.00678 -0.0885 0.6911 0.3223
-1.000 0.3463 0.01447 0.00665 -0.0876 0.6829 0.3344
-0.750 0.3706 0.01431 0.00651 -0.0866 0.6742 0.3486
-0.250 0.4185 0.01394 0.00627 -0.0846 0.6568 0.3855
0.000 0.4443 0.01366 0.00609 -0.0839 0.6492 0.4191
0.250 0.4608 0.01331 0.00610 -0.0815 0.6389 0.4870
0.500 0.4760 0.01259 0.00605 -0.0785 0.6308 0.6648
0.750 0.5403 0.01236 0.00641 -0.0844 0.6180 0.8988
1.000 0.6016 0.01256 0.00649 -0.0903 0.6054 0.9460
1.250 0.6552 0.01274 0.00648 -0.0949 0.5922 0.9689
1.500 0.7093 0.01285 0.00648 -0.1000 0.5758 0.9851
1.750 0.7652 0.01293 0.00642 -0.1056 0.5581 0.9982
2.000 0.7872 0.01300 0.00640 -0.1046 0.5426 1.0000
2.250 0.8014 0.01310 0.00640 -0.1020 0.5272 1.0000
2.500 0.8151 0.01324 0.00641 -0.0992 0.5107 1.0000
2.750 0.8279 0.01342 0.00646 -0.0963 0.4931 1.0000
3.000 0.8400 0.01363 0.00654 -0.0933 0.4750 1.0000
3.250 0.8518 0.01389 0.00666 -0.0902 0.4575 1.0000
3.500 0.8635 0.01418 0.00680 -0.0871 0.4410 1.0000
4.000 0.8885 0.01481 0.00718 -0.0812 0.4127 1.0000
4.250 0.9022 0.01515 0.00741 -0.0785 0.4011 1.0000
4.500 0.9163 0.01554 0.00764 -0.0760 0.3913 1.0000
4.750 0.9314 0.01586 0.00792 -0.0736 0.3817 1.0000
5.000 0.9475 0.01628 0.00818 -0.0714 0.3737 1.0000
5.250 0.9635 0.01661 0.00849 -0.0692 0.3659 1.0000
5.500 0.9801 0.01699 0.00879 -0.0672 0.3588 1.0000
5.750 0.9990 0.01743 0.00913 -0.0656 0.3525 1.0000
6.000 1.0147 0.01777 0.00946 -0.0634 0.3465 1.0000
6.250 1.0329 0.01817 0.00979 -0.0617 0.3412 1.0000
6.500 1.0571 0.01869 0.01020 -0.0612 0.3361 1.0000
6.750 1.0720 0.01903 0.01059 -0.0589 0.3316 1.0000
7.000 1.0899 0.01942 0.01097 -0.0572 0.3271 1.0000
7.250 1.1110 0.01986 0.01135 -0.0562 0.3230 1.0000
7.500 1.1400 0.02047 0.01185 -0.0567 0.3186 1.0000
7.750 1.1532 0.02083 0.01230 -0.0542 0.3151 1.0000
8.000 1.1704 0.02125 0.01275 -0.0524 0.3114 1.0000
8.250 1.1907 0.02170 0.01319 -0.0513 0.3079 1.0000
8.500 1.2152 0.02221 0.01365 -0.0510 0.3048 1.0000
8.750 1.2501 0.02296 0.01432 -0.0527 0.3013 1.0000
9.000 1.2624 0.02339 0.01487 -0.0501 0.2990 1.0000
9.250 1.2781 0.02389 0.01544 -0.0483 0.2963 1.0000
9.500 1.2953 0.02439 0.01599 -0.0467 0.2934 1.0000
9.750 1.3149 0.02489 0.01650 -0.0456 0.2904 1.0000
10.000 1.3396 0.02544 0.01702 -0.0454 0.2878 1.0000
10.250 1.3804 0.02637 0.01786 -0.0482 0.2845 1.0000
10.500 1.3861 0.02685 0.01849 -0.0448 0.2826 1.0000
10.750 1.3943 0.02741 0.01917 -0.0419 0.2801 1.0000
11.000 1.4044 0.02796 0.01980 -0.0394 0.2771 1.0000
11.250 1.4185 0.02846 0.02034 -0.0377 0.2739 1.0000
11.500 1.4392 0.02894 0.02079 -0.0369 0.2710 1.0000
11.750 1.4756 0.02976 0.02151 -0.0388 0.2676 1.0000
12.000 1.4775 0.03043 0.02236 -0.0353 0.2658 1.0000
12.250 1.4800 0.03118 0.02327 -0.0321 0.2634 1.0000
12.500 1.4869 0.03194 0.02414 -0.0297 0.2607 1.0000
12.750 1.4973 0.03260 0.02485 -0.0278 0.2579 1.0000
13.000 1.5140 0.03308 0.02533 -0.0268 0.2549 1.0000
13.250 1.5466 0.03359 0.02572 -0.0277 0.2516 1.0000
13.500 1.5429 0.03466 0.02697 -0.0244 0.2494 1.0000
13.750 1.5374 0.03583 0.02832 -0.0212 0.2467 1.0000
14.000 1.5381 0.03687 0.02948 -0.0188 0.2436 1.0000
14.250 1.5468 0.03764 0.03028 -0.0173 0.2406 1.0000
14.500 1.5660 0.03804 0.03063 -0.0167 0.2375 1.0000
14.750 1.5841 0.03887 0.03147 -0.0162 0.2348 1.0000
15.000 1.5736 0.04069 0.03352 -0.0134 0.2327 1.0000
15.250 1.5668 0.04251 0.03551 -0.0113 0.2301 1.0000
15.500 1.5670 0.04403 0.03715 -0.0098 0.2274 1.0000
15.750 1.5752 0.04502 0.03817 -0.0088 0.2244 1.0000
16.000 1.5964 0.04526 0.03832 -0.0084 0.2213 1.0000
16.250 1.5919 0.04731 0.04052 -0.0070 0.2187 1.0000
16.500 1.5762 0.05022 0.04367 -0.0055 0.2162 1.0000
16.750 1.5681 0.05280 0.04640 -0.0045 0.2135 1.0000
17.000 1.5699 0.05457 0.04824 -0.0038 0.2105 1.0000
17.250 1.5838 0.05530 0.04894 -0.0035 0.2075 1.0000
17.500 1.5856 0.05723 0.05094 -0.0030 0.2044 1.0000
17.750 1.5603 0.06194 0.05591 -0.0027 0.2017 1.0000
18.000 1.5449 0.06590 0.06004 -0.0028 0.1983 1.0000
18.250 1.5501 0.06765 0.06181 -0.0029 0.1946 1.0000
18.500 1.5621 0.06870 0.06282 -0.0028 0.1910 1.0000
18.750 1.5240 0.07590 0.07032 -0.0040 0.1879 1.0000
19.000 1.4983 0.08196 0.07657 -0.0055 0.1843 1.0000
19.250 1.5068 0.08361 0.07821 -0.0059 0.1801 1.0000
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Polar data table (+)
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