GOE 464 AIRFOIL (goe464-il)
GOE 464 AIRFOIL - Gottingen 464 airfoil
| Details | Dat file | Parser | |
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(goe464-il) GOE 464 AIRFOIL Gottingen 464 airfoil Max thickness 7.7% at 7.4% chord. Max camber 9.9% at 29.9% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 464 AIRFOIL
17. 17.
0.0000000 0.0000000
0.0122600 0.0335900
0.0246600 0.0486700
0.0495300 0.0678500
0.0744300 0.0815200
0.0993600 0.0917000
0.1492600 0.1060400
0.1991900 0.1153900
0.2991500 0.1220900
0.3991700 0.1187900
0.4992400 0.1089900
0.5993400 0.0937000
0.6994700 0.0759000
0.7996399 0.0516000
0.8998100 0.0268000
0.9499000 0.0141500
1.0000000 0.0000000
0.0000000 0.0000000
0.0125200 -.0061100
0.0250400 -.0063200
0.0500400 -.0051500
0.0749700 0.0045200
0.0998400 0.0227000
0.1494400 0.0454700
0.1995600 0.0629000
0.2994700 0.0761000
0.3994500 0.0788000
0.4994900 0.0735000
0.5995500 0.0637000
0.6996500 0.0499000
0.7997700 0.0331000
0.8999000 0.0148000
0.9499600 0.0056500
1.0000000 0.0000000
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Polars for GOE 464 AIRFOIL (goe464-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe464-il | 50,000 | 9 | 19.5 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe464-il | 50,000 | 5 | 37.2 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe464-il | 100,000 | 9 | 79.7 at α=1.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe464-il | 100,000 | 5 | 56 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe464-il | 200,000 | 9 | 151.5 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe464-il | 200,000 | 5 | 72.4 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe464-il | 500,000 | 9 | 164.9 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe464-il | 500,000 | 5 | 97 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe464-il | 1,000,000 | 9 | 118.4 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe464-il | 1,000,000 | 5 | 117.3 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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