GOE 483 AIRFOIL (goe483-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 483 AIRFOIL (goe483-il) Reynolds number: 1,000,000 Max Cl/Cd: 121.85 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe483-il-1000000-n5.txt Download as CSV file: xf-goe483-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 483 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.3015 0.11200 0.11040 -0.0228 1.0000 0.0037
-9.250 -0.2951 0.10904 0.10745 -0.0237 1.0000 0.0038
-9.000 -0.2891 0.10618 0.10461 -0.0245 1.0000 0.0039
-8.500 -0.2738 0.10021 0.09865 -0.0271 0.9839 0.0039
-8.250 -0.2505 0.09528 0.09371 -0.0337 0.9721 0.0040
-8.000 -0.2202 0.09027 0.08867 -0.0419 0.9594 0.0040
-7.000 -0.1592 0.07660 0.07462 -0.0565 0.8532 0.0040
-6.750 -0.1507 0.07458 0.07254 -0.0575 0.8376 0.0048
-6.500 -0.1400 0.07198 0.06988 -0.0595 0.8239 0.0049
-6.250 -0.1275 0.06920 0.06706 -0.0619 0.8127 0.0051
-5.750 -0.0958 0.06301 0.06079 -0.0680 0.7954 0.0058
-5.250 -0.0553 0.05481 0.05248 -0.0765 0.7800 0.0037
-4.750 -0.0046 0.04710 0.04463 -0.0853 0.7662 0.0035
-4.250 0.0884 0.01341 0.00936 -0.1106 0.7569 0.0032
-4.000 0.1160 0.01156 0.00710 -0.1109 0.7501 0.0035
-3.750 0.1434 0.01054 0.00577 -0.1109 0.7429 0.0037
-3.500 0.1709 0.00987 0.00487 -0.1108 0.7345 0.0040
-3.250 0.1983 0.00906 0.00381 -0.1107 0.7251 0.0043
-3.000 0.2255 0.00870 0.00334 -0.1105 0.7140 0.0049
-2.750 0.2528 0.00844 0.00297 -0.1104 0.7024 0.0055
-2.500 0.2804 0.00809 0.00248 -0.1102 0.6911 0.0062
-2.250 0.3077 0.00782 0.00207 -0.1099 0.6782 0.0069
-2.000 0.3350 0.00755 0.00169 -0.1097 0.6637 0.0088
-1.750 0.3620 0.00747 0.00150 -0.1094 0.6461 0.0109
-1.500 0.3890 0.00734 0.00128 -0.1092 0.6255 0.0181
-1.250 0.4156 0.00732 0.00117 -0.1089 0.6001 0.0284
-1.000 0.4423 0.00737 0.00110 -0.1086 0.5758 0.0328
-0.750 0.4690 0.00738 0.00102 -0.1083 0.5564 0.0392
-0.500 0.4959 0.00738 0.00097 -0.1081 0.5403 0.0485
-0.250 0.5229 0.00738 0.00094 -0.1079 0.5277 0.0630
0.000 0.5499 0.00739 0.00093 -0.1078 0.5163 0.0828
0.250 0.5771 0.00741 0.00093 -0.1076 0.5065 0.0935
0.500 0.6043 0.00745 0.00093 -0.1075 0.4976 0.1002
0.750 0.6315 0.00748 0.00094 -0.1073 0.4884 0.1072
1.000 0.6587 0.00751 0.00096 -0.1072 0.4799 0.1149
1.250 0.6857 0.00756 0.00099 -0.1070 0.4713 0.1267
1.500 0.7129 0.00759 0.00104 -0.1069 0.4620 0.1419
1.750 0.7399 0.00764 0.00111 -0.1068 0.4521 0.1644
2.000 0.7667 0.00771 0.00119 -0.1066 0.4395 0.1873
2.250 0.7935 0.00781 0.00126 -0.1064 0.4254 0.1995
2.500 0.8202 0.00792 0.00135 -0.1063 0.4120 0.2075
2.750 0.8469 0.00803 0.00143 -0.1061 0.3998 0.2150
3.000 0.8736 0.00813 0.00152 -0.1059 0.3888 0.2222
3.250 0.9002 0.00825 0.00164 -0.1057 0.3766 0.2303
3.500 0.9266 0.00838 0.00177 -0.1055 0.3641 0.2403
3.750 0.9530 0.00851 0.00190 -0.1053 0.3532 0.2538
4.000 0.9792 0.00865 0.00205 -0.1051 0.3408 0.2718
4.250 1.0041 0.00893 0.00228 -0.1048 0.3113 0.2976
4.750 1.0516 0.00863 0.00292 -0.1040 0.2357 1.0000
5.250 1.0858 0.01135 0.00450 -0.1011 0.0221 1.0000
5.500 1.1101 0.01174 0.00487 -0.1006 0.0101 1.0000
5.750 1.1349 0.01206 0.00522 -0.1001 0.0073 1.0000
6.000 1.1590 0.01247 0.00565 -0.0996 0.0055 1.0000
6.250 1.1833 0.01283 0.00605 -0.0991 0.0047 1.0000
6.500 1.2070 0.01327 0.00653 -0.0985 0.0039 1.0000
6.750 1.2302 0.01374 0.00705 -0.0978 0.0033 1.0000
7.000 1.2532 0.01422 0.00758 -0.0971 0.0029 1.0000
7.250 1.2757 0.01473 0.00814 -0.0963 0.0026 1.0000
7.500 1.2975 0.01529 0.00875 -0.0955 0.0023 1.0000
7.750 1.3163 0.01619 0.00975 -0.0941 0.0021 1.0000
8.000 1.3363 0.01690 0.01059 -0.0930 0.0019 1.0000
8.250 1.3543 0.01779 0.01158 -0.0915 0.0018 1.0000
8.500 1.3705 0.01879 0.01270 -0.0898 0.0017 1.0000
8.750 1.3847 0.01992 0.01394 -0.0879 0.0016 1.0000
9.000 1.4002 0.02083 0.01494 -0.0861 0.0015 1.0000
9.250 1.4123 0.02198 0.01620 -0.0839 0.0014 1.0000
9.500 1.4289 0.02263 0.01690 -0.0825 0.0013 1.0000
9.750 1.4388 0.02363 0.01799 -0.0800 0.0012 1.0000
10.000 1.4478 0.02452 0.01895 -0.0774 0.0011 1.0000
10.250 1.4498 0.02598 0.02054 -0.0740 0.0011 1.0000
10.500 1.4447 0.02825 0.02299 -0.0700 0.0011 1.0000
10.750 1.4462 0.03017 0.02506 -0.0672 0.0010 1.0000
11.000 1.4480 0.03222 0.02726 -0.0648 0.0010 1.0000
11.250 1.4507 0.03430 0.02951 -0.0626 0.0010 1.0000
11.500 1.4500 0.03706 0.03247 -0.0604 0.0010 1.0000
11.750 1.4461 0.04050 0.03613 -0.0582 0.0009 1.0000
12.000 1.4346 0.04705 0.04311 -0.0551 0.0008 1.0000
12.250 1.4217 0.05247 0.04882 -0.0533 0.0007 1.0000
12.500 1.4067 0.05755 0.05415 -0.0522 0.0007 1.0000
12.750 1.3906 0.06274 0.05956 -0.0520 0.0007 1.0000
13.000 1.3733 0.06835 0.06538 -0.0525 0.0007 1.0000
13.250 1.3556 0.07433 0.07154 -0.0538 0.0007 1.0000
13.500 1.3371 0.08079 0.07818 -0.0560 0.0007 1.0000
13.750 1.3192 0.08758 0.08514 -0.0589 0.0007 1.0000
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Polar data table (+)
Polar graphs
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