GOE 372 AIRFOIL (goe372-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 372 AIRFOIL (goe372-il) Reynolds number: 500,000 Max Cl/Cd: 92.95 at α=2.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe372-il-500000-n5.txt Download as CSV file: xf-goe372-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 372 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3587 0.09616 0.09395 -0.0275 1.0000 0.0040
-8.500 -0.3592 0.09268 0.09051 -0.0281 1.0000 0.0040
-8.250 -0.3604 0.08946 0.08733 -0.0284 1.0000 0.0039
-8.000 -0.3632 0.08645 0.08436 -0.0283 1.0000 0.0039
-7.750 -0.3690 0.08384 0.08181 -0.0275 1.0000 0.0039
-7.500 -0.3627 0.07956 0.07755 -0.0313 0.9961 0.0038
-7.250 -0.3444 0.07362 0.07162 -0.0394 0.9882 0.0038
-7.000 -0.3246 0.06689 0.06488 -0.0490 0.9794 0.0038
-6.750 -0.2995 0.05797 0.05592 -0.0620 0.9695 0.0038
-6.500 -0.2612 0.01921 0.01562 -0.1004 0.9519 0.0033
-6.250 -0.2346 0.01555 0.01126 -0.1016 0.9425 0.0034
-6.000 -0.2051 0.01366 0.00891 -0.1025 0.9334 0.0035
-5.750 -0.1750 0.01239 0.00727 -0.1031 0.9239 0.0038
-5.500 -0.1455 0.01138 0.00593 -0.1035 0.9131 0.0048
-5.250 -0.1171 0.01073 0.00514 -0.1036 0.9009 0.0100
-5.000 -0.0892 0.01035 0.00461 -0.1036 0.8878 0.0147
-4.750 -0.0617 0.01009 0.00418 -0.1035 0.8739 0.0167
-4.500 -0.0346 0.00995 0.00393 -0.1033 0.8607 0.0193
-4.250 -0.0079 0.00978 0.00373 -0.1031 0.8485 0.0248
-4.000 0.0188 0.00959 0.00342 -0.1028 0.8380 0.0267
-3.750 0.0456 0.00936 0.00306 -0.1025 0.8283 0.0278
-3.500 0.0721 0.00909 0.00268 -0.1021 0.8194 0.0305
-3.250 0.0988 0.00889 0.00245 -0.1018 0.8103 0.0349
-3.000 0.1256 0.00875 0.00224 -0.1015 0.8017 0.0405
-2.750 0.1524 0.00866 0.00208 -0.1013 0.7932 0.0484
-2.500 0.1793 0.00855 0.00192 -0.1010 0.7852 0.0536
-2.250 0.2062 0.00848 0.00181 -0.1007 0.7773 0.0593
-2.000 0.2331 0.00842 0.00169 -0.1005 0.7688 0.0630
-1.750 0.2599 0.00833 0.00158 -0.1002 0.7610 0.0685
-1.500 0.2868 0.00830 0.00150 -0.1000 0.7530 0.0743
-1.250 0.3137 0.00822 0.00138 -0.0997 0.7447 0.0802
-1.000 0.3404 0.00816 0.00129 -0.0995 0.7363 0.0847
-0.750 0.3673 0.00812 0.00121 -0.0992 0.7275 0.0885
-0.500 0.3940 0.00806 0.00116 -0.0989 0.7188 0.0956
-0.250 0.4206 0.00803 0.00111 -0.0986 0.7087 0.1034
0.000 0.4470 0.00801 0.00108 -0.0983 0.6958 0.1142
0.250 0.4733 0.00799 0.00107 -0.0979 0.6819 0.1290
0.500 0.4996 0.00796 0.00107 -0.0976 0.6680 0.1489
0.750 0.5256 0.00794 0.00108 -0.0972 0.6517 0.1746
1.000 0.5511 0.00791 0.00111 -0.0968 0.6307 0.2209
1.250 0.5749 0.00789 0.00118 -0.0960 0.5956 0.3064
1.500 0.5964 0.00797 0.00128 -0.0949 0.5462 0.4223
1.750 0.6366 0.00700 0.00145 -0.0980 0.5149 1.0000
2.000 0.6612 0.00724 0.00155 -0.0974 0.4917 1.0000
2.250 0.6863 0.00743 0.00169 -0.0968 0.4692 1.0000
2.500 0.7111 0.00765 0.00180 -0.0963 0.4438 1.0000
2.750 0.7354 0.00792 0.00193 -0.0956 0.4103 1.0000
3.000 0.7504 0.00914 0.00236 -0.0936 0.2480 1.0000
3.250 0.7695 0.01005 0.00281 -0.0922 0.1521 1.0000
3.500 0.7865 0.01121 0.00341 -0.0906 0.0252 1.0000
3.750 0.8111 0.01152 0.00373 -0.0899 0.0181 1.0000
4.000 0.8352 0.01187 0.00418 -0.0891 0.0148 1.0000
4.250 0.8598 0.01216 0.00450 -0.0885 0.0120 1.0000
4.500 0.8833 0.01258 0.00508 -0.0877 0.0094 1.0000
4.750 0.9042 0.01332 0.00591 -0.0863 0.0076 1.0000
5.000 0.9281 0.01366 0.00628 -0.0856 0.0062 1.0000
5.250 0.9514 0.01407 0.00671 -0.0848 0.0046 1.0000
5.500 0.9726 0.01472 0.00742 -0.0836 0.0039 1.0000
5.750 0.9932 0.01541 0.00816 -0.0823 0.0033 1.0000
6.000 1.0074 0.01682 0.00970 -0.0799 0.0027 1.0000
6.250 1.0178 0.01898 0.01198 -0.0767 0.0025 1.0000
6.500 1.0347 0.02087 0.01395 -0.0747 0.0024 1.0000
6.750 1.0553 0.02256 0.01575 -0.0734 0.0024 1.0000
7.000 1.0771 0.02457 0.01788 -0.0722 0.0024 1.0000
7.250 1.0989 0.02703 0.02053 -0.0710 0.0024 1.0000
9.250 1.2113 0.04801 0.04373 -0.0533 0.0044 1.0000
9.500 1.2071 0.05212 0.04815 -0.0496 0.0051 1.0000
9.750 1.1981 0.05580 0.05208 -0.0460 0.0057 1.0000
10.000 1.1537 0.06471 0.06113 -0.0418 0.0077 1.0000
10.250 1.1386 0.06737 0.06394 -0.0386 0.0077 1.0000
10.500 1.1215 0.07064 0.06736 -0.0365 0.0077 1.0000
10.750 1.1047 0.07422 0.07110 -0.0354 0.0077 1.0000
11.000 1.0865 0.07848 0.07550 -0.0355 0.0077 1.0000
11.250 1.0691 0.08307 0.08022 -0.0365 0.0077 1.0000
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Polar data table (+)
Polar graphs
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