GOE 444 AIRFOIL (goe444-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: GOE 444 AIRFOIL (goe444-il) Reynolds number: 100,000 Max Cl/Cd: 21.47 at α=2.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe444-il-100000.txt Download as CSV file: xf-goe444-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 444 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.6445 0.08898 0.08422 -0.0033 1.0000 0.0757
-8.000 -0.6545 0.08465 0.07993 -0.0076 1.0000 0.0773
-7.750 -0.6649 0.08051 0.07568 -0.0128 1.0000 0.0789
-7.500 -0.6771 0.07805 0.07285 -0.0158 1.0000 0.0797
-7.250 -0.6544 0.07173 0.06696 -0.0119 1.0000 0.0863
-7.000 -0.6627 0.06891 0.06363 -0.0157 1.0000 0.0926
-6.750 -0.6480 0.06348 0.05851 -0.0139 1.0000 0.0978
-6.500 -0.6420 0.05999 0.05494 -0.0137 1.0000 0.1117
-4.500 -0.5078 0.02926 0.02103 -0.0058 1.0000 0.0732
-4.250 -0.4809 0.02629 0.01740 -0.0036 1.0000 0.0577
-4.000 -0.4543 0.02440 0.01488 -0.0016 1.0000 0.0519
-3.750 -0.4290 0.02203 0.01228 -0.0004 1.0000 0.0502
-3.500 -0.4034 0.02019 0.01025 0.0009 1.0000 0.0507
-3.250 -0.3803 0.01851 0.00857 0.0021 1.0000 0.0593
-3.000 -0.3576 0.01711 0.00716 0.0037 1.0000 0.0637
-2.750 -0.3378 0.01573 0.00578 0.0057 1.0000 0.0703
-2.500 -0.1692 0.01201 0.00485 -0.0167 1.0000 1.0000
-2.250 -0.1532 0.01170 0.00436 -0.0153 1.0000 1.0000
-2.000 -0.1370 0.01143 0.00395 -0.0138 1.0000 1.0000
-1.750 -0.1207 0.01121 0.00360 -0.0121 1.0000 1.0000
-1.500 -0.1042 0.01103 0.00332 -0.0104 1.0000 1.0000
-1.250 -0.0874 0.01088 0.00308 -0.0087 1.0000 1.0000
-1.000 -0.0705 0.01077 0.00290 -0.0069 1.0000 1.0000
-0.750 -0.0533 0.01068 0.00273 -0.0052 1.0000 1.0000
-0.500 -0.0357 0.01062 0.00263 -0.0034 1.0000 1.0000
-0.250 -0.0179 0.01059 0.00256 -0.0017 1.0000 1.0000
0.000 0.0000 0.01058 0.00254 0.0000 1.0000 1.0000
0.250 0.0179 0.01059 0.00256 0.0017 1.0000 1.0000
0.500 0.0357 0.01062 0.00262 0.0034 1.0000 1.0000
0.750 0.0533 0.01068 0.00273 0.0052 1.0000 1.0000
1.000 0.0705 0.01077 0.00290 0.0069 1.0000 1.0000
1.250 0.0875 0.01088 0.00308 0.0087 1.0000 1.0000
1.500 0.1042 0.01103 0.00331 0.0104 1.0000 1.0000
1.750 0.1208 0.01121 0.00360 0.0121 1.0000 1.0000
2.000 0.1371 0.01143 0.00395 0.0138 1.0000 1.0000
2.250 0.1533 0.01169 0.00436 0.0153 1.0000 1.0000
2.500 0.1693 0.01201 0.00484 0.0167 1.0000 1.0000
2.750 0.3378 0.01573 0.00577 -0.0057 0.0703 1.0000
3.000 0.3576 0.01711 0.00716 -0.0037 0.0637 1.0000
3.250 0.3802 0.01851 0.00856 -0.0021 0.0589 1.0000
3.500 0.4034 0.02019 0.01025 -0.0009 0.0507 1.0000
3.750 0.4290 0.02202 0.01227 0.0004 0.0502 1.0000
4.000 0.4543 0.02440 0.01488 0.0016 0.0518 1.0000
4.250 0.4809 0.02628 0.01738 0.0035 0.0576 1.0000
6.000 0.6266 0.05395 0.04877 0.0121 0.1539 1.0000
6.750 0.6479 0.06358 0.05862 0.0137 0.0987 1.0000
7.000 0.6628 0.06889 0.06362 0.0157 0.0926 1.0000
7.250 0.6546 0.07174 0.06696 0.0119 0.0865 1.0000
7.500 0.6772 0.07804 0.07284 0.0158 0.0797 1.0000
7.750 0.6653 0.08053 0.07570 0.0128 0.0789 1.0000
8.000 0.6542 0.08473 0.08001 0.0073 0.0772 1.0000
8.250 0.6441 0.08907 0.08430 0.0031 0.0753 1.0000
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Polar data table (+)
Polar graphs
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