RAF 19 AIRFOIL (raf19-il)
RAF 19 AIRFOIL - RAF-19 airfoil
Details | Dat file | Parser | |
(raf19-il) RAF 19 AIRFOIL RAF-19 airfoil Max thickness 10.5% at 15% chord. Max camber 10.1% at 40% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
RAF 19 AIRFOIL 17. 17. 0.0000000 0.0000000 0.0125000 0.0270700 0.0250000 0.0461500 0.0500000 0.0733000 0.0750000 0.0924500 0.1000000 0.1066000 0.1500000 0.1259000 0.2000000 0.1362000 0.3000000 0.1418000 0.4000000 0.1374000 0.5000000 0.1250000 0.6000000 0.1086000 0.7000000 0.0872000 0.8000000 0.0638000 0.9000000 0.0364000 0.9500000 0.0197000 1.0000000 0.0000000 0.0000000 0.0000000 0.0125000 -.0080300 0.0250000 -.0118500 0.0500000 -.0107000 0.0750000 -.0055500 0.1000000 0.0026000 0.1500000 0.0209000 0.2000000 0.0382000 0.3000000 0.0588000 0.4000000 0.0654000 0.5000000 0.0630000 0.6000000 0.0536000 0.7000000 0.0422000 0.8000000 0.0268000 0.9000000 0.0104000 0.9500000 0.0017000 1.0000000 0.0000000 |
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Similar airfoils
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Polars for RAF 19 AIRFOIL (raf19-il)
Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
---|---|---|---|---|---|---|---|
raf19-il | 50,000 | 9 | 13.1 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
raf19-il | 50,000 | 5 | 32.2 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
raf19-il | 100,000 | 9 | 44.6 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
raf19-il | 100,000 | 5 | 48.7 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
raf19-il | 200,000 | 9 | 62.4 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
raf19-il | 200,000 | 5 | 61.8 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
raf19-il | 500,000 | 9 | 82.2 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
raf19-il | 500,000 | 5 | 83.3 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
raf19-il | 1,000,000 | 9 | 104.8 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
raf19-il | 1,000,000 | 5 | 103 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
Reynolds number calculator |