GOE 362 AIRFOIL (goe362-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: GOE 362 AIRFOIL (goe362-il) Reynolds number: 50,000 Max Cl/Cd: 43.36 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe362-il-50000-n5.txt Download as CSV file: xf-goe362-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 362 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.250 -0.2864 0.09860 0.09221 -0.0250 1.0000 0.0804
-7.000 -0.2887 0.09687 0.09060 -0.0245 1.0000 0.0831
-6.750 -0.2919 0.09575 0.08961 -0.0258 1.0000 0.0858
-6.500 -0.2938 0.09490 0.08889 -0.0287 1.0000 0.0869
-6.250 -0.2915 0.09373 0.08780 -0.0328 1.0000 0.0873
-6.000 -0.2890 0.08857 0.08275 -0.0262 1.0000 0.0894
-5.750 -0.2867 0.08596 0.08021 -0.0246 1.0000 0.0917
-5.500 -0.2845 0.08371 0.07802 -0.0244 1.0000 0.0941
-5.250 -0.2810 0.08154 0.07592 -0.0254 1.0000 0.0968
-5.000 -0.2682 0.08000 0.07436 -0.0322 1.0000 0.1005
-4.750 -0.2517 0.07755 0.07189 -0.0378 1.0000 0.1012
-4.250 -0.2194 0.06937 0.06372 -0.0397 0.9932 0.1031
-4.000 -0.1662 0.06169 0.05571 -0.0508 0.9863 0.0581
-3.750 -0.1265 0.05709 0.05097 -0.0575 0.9785 0.0560
-3.500 -0.0798 0.05231 0.04596 -0.0658 0.9705 0.0561
-3.250 -0.0310 0.04749 0.04085 -0.0738 0.9631 0.0548
-3.000 0.0205 0.04258 0.03553 -0.0815 0.9549 0.0536
-2.750 0.0704 0.03820 0.03060 -0.0879 0.9458 0.0554
-2.500 0.1265 0.03369 0.02520 -0.0946 0.9387 0.0594
-2.250 0.1679 0.03077 0.02179 -0.0978 0.9282 0.0621
-2.000 0.2095 0.02884 0.01934 -0.1005 0.9181 0.0720
-1.750 0.2536 0.02685 0.01688 -0.1034 0.9103 0.0800
-1.500 0.2897 0.02570 0.01537 -0.1048 0.8990 0.0964
-1.250 0.3279 0.02438 0.01365 -0.1061 0.8891 0.1098
-1.000 0.3683 0.02347 0.01254 -0.1080 0.8800 0.1376
-0.750 0.4036 0.02277 0.01171 -0.1090 0.8684 0.1676
-0.500 0.4372 0.02221 0.01112 -0.1097 0.8562 0.2091
-0.250 0.4706 0.02157 0.01055 -0.1104 0.8440 0.2619
0.000 0.5035 0.02071 0.01016 -0.1111 0.8318 0.3679
0.250 0.5338 0.01925 0.00966 -0.1107 0.8191 1.0000
0.500 0.5650 0.01933 0.00935 -0.1107 0.8055 1.0000
0.750 0.5951 0.01942 0.00916 -0.1105 0.7914 1.0000
1.000 0.6243 0.01953 0.00903 -0.1102 0.7768 1.0000
1.250 0.6529 0.01966 0.00896 -0.1097 0.7618 1.0000
1.500 0.6809 0.01981 0.00895 -0.1092 0.7464 1.0000
1.750 0.7084 0.01997 0.00898 -0.1087 0.7308 1.0000
2.000 0.7357 0.02016 0.00904 -0.1081 0.7150 1.0000
2.250 0.7626 0.02037 0.00914 -0.1074 0.6992 1.0000
2.500 0.7894 0.02059 0.00929 -0.1068 0.6835 1.0000
2.750 0.8160 0.02085 0.00946 -0.1061 0.6678 1.0000
3.000 0.8424 0.02113 0.00968 -0.1055 0.6524 1.0000
3.250 0.8685 0.02144 0.00996 -0.1048 0.6371 1.0000
3.500 0.8944 0.02178 0.01027 -0.1041 0.6220 1.0000
3.750 0.9200 0.02215 0.01063 -0.1034 0.6072 1.0000
4.000 0.9453 0.02255 0.01107 -0.1028 0.5926 1.0000
4.250 0.9704 0.02297 0.01151 -0.1021 0.5782 1.0000
4.500 0.9952 0.02341 0.01200 -0.1013 0.5642 1.0000
4.750 1.0199 0.02387 0.01251 -0.1006 0.5504 1.0000
5.000 1.0444 0.02434 0.01310 -0.0999 0.5370 1.0000
5.250 1.0689 0.02482 0.01366 -0.0991 0.5240 1.0000
5.500 1.0933 0.02531 0.01424 -0.0983 0.5111 1.0000
5.750 1.1178 0.02580 0.01486 -0.0976 0.4986 1.0000
6.000 1.1417 0.02633 0.01552 -0.0967 0.4857 1.0000
6.250 1.1649 0.02693 0.01628 -0.0958 0.4723 1.0000
6.500 1.1878 0.02755 0.01706 -0.0949 0.4588 1.0000
6.750 1.2102 0.02809 0.01777 -0.0938 0.4432 1.0000
7.000 1.2303 0.02856 0.01834 -0.0922 0.4233 1.0000
7.250 1.2482 0.02904 0.01893 -0.0904 0.4004 1.0000
7.500 1.2657 0.02957 0.01958 -0.0886 0.3784 1.0000
7.750 1.2825 0.03025 0.02046 -0.0869 0.3575 1.0000
8.000 1.2989 0.03089 0.02131 -0.0851 0.3365 1.0000
8.250 1.3128 0.03169 0.02235 -0.0831 0.3125 1.0000
8.500 1.3253 0.03256 0.02338 -0.0810 0.2870 1.0000
8.750 1.3358 0.03359 0.02451 -0.0787 0.2599 1.0000
9.000 1.3432 0.03488 0.02582 -0.0761 0.2312 1.0000
9.250 1.3478 0.03649 0.02738 -0.0735 0.2046 1.0000
9.500 1.3512 0.03834 0.02922 -0.0709 0.1830 1.0000
9.750 1.3521 0.04033 0.03118 -0.0681 0.1666 1.0000
10.000 1.3522 0.04250 0.03334 -0.0656 0.1522 1.0000
10.250 1.3520 0.04482 0.03572 -0.0634 0.1391 1.0000
10.500 1.3514 0.04732 0.03832 -0.0614 0.1274 1.0000
10.750 1.3468 0.05015 0.04132 -0.0599 0.1155 1.0000
11.000 1.3392 0.05338 0.04460 -0.0589 0.1040 1.0000
11.250 1.3305 0.05697 0.04823 -0.0584 0.0938 1.0000
11.500 1.3224 0.06080 0.05208 -0.0582 0.0852 1.0000
11.750 1.3162 0.06481 0.05630 -0.0581 0.0766 1.0000
12.000 1.3084 0.06904 0.06054 -0.0583 0.0700 1.0000
12.250 1.3020 0.07348 0.06524 -0.0587 0.0626 1.0000
12.500 1.2949 0.07786 0.06956 -0.0591 0.0577 1.0000
12.750 1.2895 0.08262 0.07470 -0.0598 0.0523 1.0000
13.000 1.2834 0.08726 0.07946 -0.0608 0.0485 1.0000
13.250 1.2784 0.09170 0.08388 -0.0616 0.0455 1.0000
13.500 1.2721 0.09711 0.08967 -0.0628 0.0432 1.0000
13.750 1.2642 0.10283 0.09567 -0.0647 0.0414 1.0000
14.000 1.2552 0.10883 0.10190 -0.0671 0.0400 1.0000
14.250 1.2460 0.11499 0.10825 -0.0698 0.0388 1.0000
14.500 1.2377 0.12107 0.11447 -0.0727 0.0377 1.0000
14.750 1.2338 0.12599 0.11937 -0.0748 0.0363 1.0000
15.000 1.2202 0.13410 0.12771 -0.0793 0.0361 1.0000
15.250 1.2061 0.14274 0.13654 -0.0844 0.0362 1.0000
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Polar data table (+)
Polar graphs
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