GOE 584 AIRFOIL (goe584-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 584 AIRFOIL (goe584-il) Reynolds number: 100,000 Max Cl/Cd: 55.04 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe584-il-100000-n5.txt Download as CSV file: xf-goe584-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 584 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
------ -------- --------- --------- -------- -------- --------
-10.500 -0.2860 0.10659 0.10152 -0.0483 1.0000 0.0519
-10.250 -0.2926 0.10331 0.09832 -0.0487 1.0000 0.0521
-10.000 -0.3075 0.10007 0.09520 -0.0489 1.0000 0.0527
-9.750 -0.2908 0.09805 0.09321 -0.0495 0.9936 0.0550
-9.500 -0.2723 0.09466 0.08980 -0.0531 0.9842 0.0569
-9.250 -0.2613 0.08979 0.08492 -0.0583 0.9731 0.0573
-9.000 -0.2490 0.08506 0.08017 -0.0639 0.9626 0.0588
-8.750 -0.2397 0.07948 0.07456 -0.0711 0.9507 0.0605
-8.500 -0.2346 0.07325 0.06830 -0.0790 0.9363 0.0612
-8.250 -0.2372 0.06526 0.06022 -0.0894 0.9189 0.0621
-7.750 -0.2420 0.04929 0.04364 -0.1033 0.8914 0.0648
-7.500 -0.2232 0.04818 0.04249 -0.1032 0.8809 0.0661
-7.250 -0.2040 0.04595 0.04010 -0.1044 0.8729 0.0681
-7.000 -0.1945 0.04245 0.03628 -0.1051 0.8618 0.0699
-6.750 -0.1829 0.03854 0.03193 -0.1057 0.8529 0.0712
-6.500 -0.1693 0.03539 0.02827 -0.1055 0.8437 0.0735
-6.250 -0.1525 0.03277 0.02507 -0.1051 0.8358 0.0751
-6.000 -0.1333 0.03080 0.02261 -0.1044 0.8275 0.0760
-5.750 -0.1107 0.02906 0.02062 -0.1042 0.8210 0.0774
-5.500 -0.0889 0.02806 0.01952 -0.1035 0.8126 0.0791
-5.250 -0.0633 0.02701 0.01825 -0.1034 0.8065 0.0807
-5.000 -0.0409 0.02599 0.01701 -0.1026 0.7984 0.0818
-4.750 -0.0157 0.02498 0.01575 -0.1021 0.7917 0.0830
-4.500 0.0097 0.02409 0.01464 -0.1017 0.7854 0.0843
-4.250 0.0341 0.02340 0.01376 -0.1010 0.7779 0.0863
-4.000 0.0614 0.02271 0.01282 -0.1008 0.7723 0.0884
-3.750 0.0859 0.02215 0.01210 -0.1001 0.7648 0.0898
-3.500 0.1121 0.02149 0.01132 -0.0996 0.7584 0.0909
-3.250 0.1389 0.02085 0.01064 -0.0994 0.7531 0.0925
-3.000 0.1628 0.02044 0.01023 -0.0986 0.7455 0.0942
-2.750 0.1896 0.02001 0.00975 -0.0982 0.7399 0.0964
-2.500 0.2149 0.01971 0.00941 -0.0977 0.7337 0.0997
-2.250 0.2399 0.01944 0.00909 -0.0970 0.7271 0.1033
-2.000 0.2668 0.01908 0.00868 -0.0966 0.7220 0.1068
-1.750 0.2905 0.01885 0.00850 -0.0959 0.7152 0.1106
-1.500 0.3159 0.01864 0.00826 -0.0952 0.7091 0.1157
-1.250 0.3433 0.01836 0.00795 -0.0949 0.7044 0.1230
-1.000 0.3664 0.01825 0.00790 -0.0940 0.6972 0.1349
-0.750 0.3922 0.01800 0.00778 -0.0935 0.6914 0.1610
-0.500 0.4196 0.01771 0.00763 -0.0933 0.6867 0.2146
-0.250 0.4430 0.01750 0.00772 -0.0927 0.6794 0.2858
0.000 0.4690 0.01711 0.00765 -0.0924 0.6739 0.3983
0.250 0.4895 0.01614 0.00775 -0.0904 0.6687 0.7118
0.500 0.5759 0.01583 0.00771 -0.1018 0.6612 1.0000
0.750 0.6011 0.01591 0.00762 -0.1010 0.6556 1.0000
1.000 0.6230 0.01610 0.00772 -0.0999 0.6485 1.0000
1.250 0.6465 0.01624 0.00775 -0.0989 0.6417 1.0000
1.500 0.6721 0.01634 0.00771 -0.0983 0.6362 1.0000
1.750 0.6930 0.01657 0.00791 -0.0970 0.6284 1.0000
2.000 0.7184 0.01668 0.00792 -0.0963 0.6226 1.0000
2.250 0.7410 0.01690 0.00809 -0.0953 0.6157 1.0000
2.500 0.7644 0.01707 0.00821 -0.0944 0.6088 1.0000
2.750 0.7906 0.01718 0.00822 -0.0939 0.6032 1.0000
3.000 0.8111 0.01746 0.00852 -0.0926 0.5951 1.0000
3.250 0.8368 0.01758 0.00857 -0.0920 0.5889 1.0000
3.500 0.8585 0.01784 0.00883 -0.0909 0.5813 1.0000
3.750 0.8824 0.01801 0.00898 -0.0900 0.5741 1.0000
4.000 0.9060 0.01821 0.00916 -0.0892 0.5671 1.0000
4.250 0.9281 0.01845 0.00940 -0.0881 0.5590 1.0000
4.500 0.9530 0.01860 0.00952 -0.0874 0.5521 1.0000
4.750 0.9735 0.01888 0.00985 -0.0861 0.5432 1.0000
5.000 0.9985 0.01904 0.00996 -0.0855 0.5362 1.0000
5.250 1.0182 0.01934 0.01033 -0.0841 0.5268 1.0000
5.500 1.0422 0.01952 0.01050 -0.0833 0.5191 1.0000
5.750 1.0619 0.01982 0.01086 -0.0819 0.5094 1.0000
6.000 1.0838 0.02006 0.01111 -0.0808 0.5006 1.0000
6.250 1.1045 0.02032 0.01140 -0.0795 0.4909 1.0000
6.500 1.1235 0.02063 0.01176 -0.0780 0.4803 1.0000
6.750 1.1436 0.02086 0.01198 -0.0766 0.4691 1.0000
7.000 1.1618 0.02111 0.01221 -0.0749 0.4562 1.0000
7.250 1.1772 0.02146 0.01260 -0.0728 0.4422 1.0000
7.500 1.1924 0.02184 0.01300 -0.0708 0.4286 1.0000
7.750 1.2079 0.02225 0.01343 -0.0688 0.4164 1.0000
8.000 1.2234 0.02267 0.01385 -0.0669 0.4048 1.0000
8.250 1.2368 0.02313 0.01432 -0.0646 0.3930 1.0000
8.500 1.2476 0.02367 0.01490 -0.0620 0.3811 1.0000
8.750 1.2585 0.02425 0.01550 -0.0595 0.3695 1.0000
9.000 1.2698 0.02487 0.01609 -0.0571 0.3584 1.0000
9.250 1.2793 0.02559 0.01686 -0.0547 0.3468 1.0000
9.500 1.2889 0.02637 0.01768 -0.0524 0.3358 1.0000
9.750 1.2983 0.02720 0.01851 -0.0502 0.3250 1.0000
10.000 1.3064 0.02814 0.01949 -0.0480 0.3138 1.0000
10.250 1.3138 0.02917 0.02057 -0.0459 0.3027 1.0000
10.500 1.3214 0.03024 0.02164 -0.0439 0.2923 1.0000
10.750 1.3277 0.03144 0.02288 -0.0420 0.2815 1.0000
11.000 1.3339 0.03272 0.02424 -0.0402 0.2711 1.0000
11.250 1.3401 0.03404 0.02558 -0.0385 0.2615 1.0000
11.500 1.3441 0.03555 0.02713 -0.0368 0.2508 1.0000
11.750 1.3471 0.03719 0.02884 -0.0352 0.2400 1.0000
12.000 1.3490 0.03898 0.03064 -0.0337 0.2292 1.0000
12.250 1.3492 0.04094 0.03257 -0.0322 0.2186 1.0000
12.500 1.3496 0.04302 0.03475 -0.0310 0.2077 1.0000
12.750 1.3495 0.04521 0.03698 -0.0300 0.1976 1.0000
13.000 1.3490 0.04748 0.03923 -0.0290 0.1891 1.0000
13.250 1.3497 0.04982 0.04169 -0.0282 0.1800 1.0000
13.500 1.3498 0.05219 0.04404 -0.0275 0.1733 1.0000
13.750 1.3510 0.05464 0.04665 -0.0270 0.1656 1.0000
14.000 1.3489 0.05742 0.04943 -0.0266 0.1585 1.0000
14.250 1.3483 0.06021 0.05235 -0.0264 0.1511 1.0000
14.500 1.3453 0.06333 0.05555 -0.0263 0.1440 1.0000
14.750 1.3429 0.06646 0.05875 -0.0264 0.1377 1.0000
15.000 1.3400 0.06982 0.06224 -0.0266 0.1308 1.0000
15.250 1.3333 0.07366 0.06608 -0.0271 0.1244 1.0000
15.500 1.3287 0.07750 0.07009 -0.0277 0.1169 1.0000
15.750 1.3214 0.08171 0.07436 -0.0286 0.1106 1.0000
16.000 1.3147 0.08603 0.07882 -0.0296 0.1035 1.0000
16.250 1.3049 0.09088 0.08374 -0.0309 0.0967 1.0000
16.500 1.2960 0.09580 0.08879 -0.0324 0.0887 1.0000
16.750 1.2844 0.10125 0.09434 -0.0342 0.0803 1.0000
17.000 1.2726 0.10687 0.10002 -0.0363 0.0719 1.0000
17.250 1.2604 0.11264 0.10584 -0.0385 0.0640 1.0000
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