RAF 30 AIRFOIL (raf30-il)
RAF 30 AIRFOIL - RAF-30 airfoil
| Details | Dat file | Parser | |
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(raf30-il) RAF 30 AIRFOIL RAF-30 airfoil Max thickness 12.6% at 30% chord. Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
RAF 30 AIRFOIL
16. 16.
0.0000000 0.0000000
0.0125000 0.0180000
0.0250000 0.0248000
0.0500000 0.0346000
0.1000000 0.0468000
0.1500000 0.0544000
0.2000000 0.0594000
0.3000000 0.0632000
0.4000000 0.0620000
0.5000000 0.0566000
0.6000000 0.0478000
0.7000000 0.0370000
0.8000000 0.0250000
0.9000000 0.0130000
0.9500000 0.0070000
1.0000000 0.0000000
0.0000000 0.0000000
0.0125000 -.0180000
0.0250000 -.0248000
0.0500000 -.0346000
0.1000000 -.0468000
0.1500000 -.0544000
0.2000000 -.0594000
0.3000000 -.0632000
0.4000000 -.0620000
0.5000000 -.0566000
0.6000000 -.0478000
0.7000000 -.0370000
0.8000000 -.0250000
0.9000000 -.0130000
0.9500000 -.0070000
1.0000000 0.0000000
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Polars for RAF 30 AIRFOIL (raf30-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| raf30-il | 50,000 | 9 | 28.4 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf30-il | 50,000 | 5 | 28.7 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf30-il | 100,000 | 9 | 41.7 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf30-il | 100,000 | 5 | 39.1 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf30-il | 200,000 | 9 | 52.3 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf30-il | 200,000 | 5 | 45.6 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf30-il | 500,000 | 9 | 58.5 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf30-il | 500,000 | 5 | 58.3 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf30-il | 1,000,000 | 9 | 69.5 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf30-il | 1,000,000 | 5 | 71.6 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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