RAF 34 AIRFOIL (raf34-il)
RAF 34 AIRFOIL - RAF-34 airfoil
| Details | Dat file | Parser | |
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(raf34-il) RAF 34 AIRFOIL RAF-34 airfoil Max thickness 12.6% at 30% chord. Max camber 2% at 30% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
RAF 34 AIRFOIL
17. 17.
0.0000000 0.0000000
0.0125000 0.0196000
0.0250000 0.0282000
0.0500000 0.0411000
0.0750000 0.0512000
0.1000000 0.0583000
0.1500000 0.0697000
0.2000000 0.0772000
0.3000000 0.0832000
0.4000000 0.0808000
0.5000000 0.0721000
0.6000000 0.0587000
0.7000000 0.0431000
0.8000000 0.0270000
0.9000000 0.0126000
0.9500000 0.0064000
1.0000000 0.0000000
0.0000000 0.0000000
0.0125000 -.0162000
0.0250000 -.0214000
0.0500000 -.0281000
0.0750000 -.0325000
0.1000000 -.0353000
0.1500000 -.0391000
0.2000000 -.0416000
0.3000000 -.0432000
0.4000000 -.0432000
0.5000000 -.0411000
0.6000000 -.0369000
0.7000000 -.0309000
0.8000000 -.0230000
0.9000000 -.0134000
0.9500000 -.0076000
1.0000000 0.0000000
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Polars for RAF 34 AIRFOIL (raf34-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| raf34-il | 50,000 | 9 | 25.7 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf34-il | 50,000 | 5 | 30.7 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf34-il | 100,000 | 9 | 48.2 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf34-il | 100,000 | 5 | 49.1 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf34-il | 200,000 | 9 | 67.5 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf34-il | 200,000 | 5 | 65.2 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf34-il | 500,000 | 9 | 90.8 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf34-il | 500,000 | 5 | 79.4 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf34-il | 1,000,000 | 9 | 99.8 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf34-il | 1,000,000 | 5 | 84.8 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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