GOE 101 AIRFOIL (goe101-il)
GOE 101 AIRFOIL - Gottingen 101 airfoil
Details | Dat file | Parser | |
(goe101-il) GOE 101 AIRFOIL Gottingen 101 airfoil Max thickness 6.9% at 30% chord. Max camber 4% at 30% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GOE 101 AIRFOIL 16. 16. 0.0000000 0.0000000 0.0125000 0.0150900 0.0250000 0.0231800 0.0500000 0.0353500 0.0750000 0.0435200 0.1000000 0.0507000 0.1500000 0.0605500 0.2000000 0.0674000 0.3000000 0.0741000 0.4000000 0.0713000 0.5000000 0.0640000 0.6000000 0.0542000 0.7000000 0.0424000 0.8000000 0.0296000 0.9000000 0.0153000 1.0000000 0.0000000 0.0000000 0.0000000 0.0125000 -.0069100 0.0250000 -.0067300 0.0500000 -.0054500 0.0750000 -.0037700 0.1000000 -.0023000 0.1500000 0.0000500 0.2000000 0.0019000 0.3000000 0.0051000 0.4000000 0.0075000 0.5000000 0.0085000 0.6000000 0.0082000 0.7000000 0.0069000 0.8000000 0.0051000 0.9000000 0.0028000 1.0000000 0.0000000 |
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Similar airfoils
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Polars for GOE 101 AIRFOIL (goe101-il)
Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
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goe101-il | 50,000 | 9 | 39.7 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
goe101-il | 50,000 | 5 | 41.1 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
goe101-il | 100,000 | 9 | 58.7 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
goe101-il | 100,000 | 5 | 59.5 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
goe101-il | 200,000 | 9 | 77.9 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
goe101-il | 200,000 | 5 | 77.2 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
goe101-il | 500,000 | 9 | 104.4 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
goe101-il | 500,000 | 5 | 100.5 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
goe101-il | 1,000,000 | 9 | 123.8 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
goe101-il | 1,000,000 | 5 | 114.7 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
Reynolds number calculator |