GOE 483 AIRFOIL (goe483-il) Xfoil prediction polar at RE=500,000 Ncrit=9
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Airfoil: GOE 483 AIRFOIL (goe483-il) Reynolds number: 500,000 Max Cl/Cd: 114.35 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe483-il-500000.txt Download as CSV file: xf-goe483-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
0.250 0.5311 0.00784 0.00156 -0.0973 0.7162 0.1461
0.500 0.5578 0.00782 0.00154 -0.0969 0.7006 0.1618
0.750 0.5844 0.00784 0.00154 -0.0966 0.6830 0.1821
1.000 0.6108 0.00789 0.00156 -0.0962 0.6634 0.2054
1.250 0.6372 0.00795 0.00157 -0.0958 0.6410 0.2243
1.500 0.6633 0.00804 0.00158 -0.0953 0.6179 0.2410
1.750 0.6893 0.00815 0.00161 -0.0949 0.5951 0.2553
2.000 0.7154 0.00825 0.00167 -0.0945 0.5751 0.2694
2.250 0.7414 0.00836 0.00174 -0.0942 0.5571 0.2851
2.500 0.7674 0.00846 0.00183 -0.0939 0.5407 0.3087
2.750 0.7951 0.00728 0.00198 -0.0941 0.5259 1.0000
3.000 0.8214 0.00746 0.00207 -0.0938 0.5127 1.0000
3.250 0.8477 0.00763 0.00221 -0.0935 0.5001 1.0000
3.500 0.8740 0.00780 0.00233 -0.0932 0.4880 1.0000
3.750 0.9003 0.00797 0.00247 -0.0929 0.4762 1.0000
4.000 0.9265 0.00815 0.00261 -0.0925 0.4638 1.0000
4.250 0.9525 0.00833 0.00276 -0.0922 0.4488 1.0000
4.500 0.9778 0.00856 0.00293 -0.0917 0.4245 1.0000
4.750 1.0030 0.00881 0.00310 -0.0913 0.4002 1.0000
5.000 1.0279 0.00910 0.00331 -0.0909 0.3740 1.0000
5.250 1.0518 0.00950 0.00356 -0.0903 0.3376 1.0000
5.500 1.0747 0.01004 0.00390 -0.0896 0.2918 1.0000
5.750 1.0929 0.01121 0.00449 -0.0884 0.1907 1.0000
6.000 1.1015 0.01377 0.00603 -0.0859 0.0232 1.0000
6.250 1.1249 0.01431 0.00668 -0.0851 0.0190 1.0000
6.500 1.1474 0.01495 0.00744 -0.0842 0.0168 1.0000
6.750 1.1679 0.01587 0.00848 -0.0829 0.0150 1.0000
7.000 1.1832 0.01738 0.01019 -0.0809 0.0136 1.0000
7.250 1.2031 0.01819 0.01109 -0.0797 0.0127 1.0000
7.500 1.2212 0.01919 0.01218 -0.0782 0.0122 1.0000
7.750 1.2375 0.02036 0.01345 -0.0764 0.0117 1.0000
8.000 1.2527 0.02166 0.01485 -0.0745 0.0110 1.0000
8.250 1.2670 0.02315 0.01644 -0.0725 0.0107 1.0000
8.500 1.2814 0.02492 0.01830 -0.0704 0.0106 1.0000
8.750 1.2982 0.02716 0.02066 -0.0687 0.0110 1.0000
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Polar data table (+)
Polar graphs
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