RAF 32 AIRFOIL (raf32-il)
RAF 32 AIRFOIL - RAF-32 airfoil
| Details | Dat file | Parser | |
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(raf32-il) RAF 32 AIRFOIL RAF-32 airfoil Max thickness 12.7% at 30% chord. Max camber 5% at 50% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
RAF 32 AIRFOIL
13. 13.
0.0000000 0.0000000
0.0250000 0.0318200
0.0500000 0.0458500
0.1000000 0.0663000
0.2000000 0.0916000
0.3000000 0.1055000
0.4000000 0.1100000
0.5000000 0.1069000
0.6000000 0.0962000
0.7000000 0.0799000
0.8000000 0.0578000
0.9000000 0.0315000
1.0000000 0.0000000
0.0000000 0.0000000
0.0250000 -.0183700
0.0500000 -.0237500
0.1000000 -.0279000
0.2000000 -.0276000
0.3000000 -.0213000
0.4000000 -.0140000
0.5000000 -.0067000
0.6000000 0.0002000
0.7000000 0.0049000
0.8000000 0.0068000
0.9000000 0.0047000
1.0000000 0.0000000
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Similar airfoils
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Polars for RAF 32 AIRFOIL (raf32-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| raf32-il | 50,000 | 9 | 29.2 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf32-il | 50,000 | 5 | 25.6 at α=10° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf32-il | 100,000 | 9 | 56.2 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf32-il | 100,000 | 5 | 56.3 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf32-il | 200,000 | 9 | 85.7 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf32-il | 200,000 | 5 | 84.8 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf32-il | 500,000 | 9 | 123.7 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf32-il | 500,000 | 5 | 116.6 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf32-il | 1,000,000 | 9 | 152.3 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf32-il | 1,000,000 | 5 | 134.8 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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