RAF 30 MOD AIRFOIL (raf30md-il)
RAF 30 MOD AIRFOIL - RAF-30 MOD airfoil
| Details | Dat file | Parser | |
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(raf30md-il) RAF 30 MOD AIRFOIL RAF-30 MOD airfoil Max thickness 7.6% 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 MOD AIRFOIL
15. 15.
0.0000000 0.0000000
0.0125000 0.0108000
0.0250000 0.0149000
0.0500000 0.0208000
0.1000000 0.0281000
0.1500000 0.0326000
0.2000000 0.0356000
0.3000000 0.0380000
0.4000000 0.0372000
0.5000000 0.0340000
0.6000000 0.0287000
0.7000000 0.0222000
0.8000000 0.0150000
0.9000000 0.0078000
1.0000000 0.0000000
0.0000000 0.0000000
0.0125000 -.0108000
0.0250000 -.0149000
0.0500000 -.0208000
0.1000000 -.0281000
0.1500000 -.0326000
0.2000000 -.0356000
0.3000000 -.0380000
0.4000000 -.0372000
0.5000000 -.0340000
0.6000000 -.0287000
0.7000000 -.0222000
0.8000000 -.0150000
0.9000000 -.0078000
1.0000000 0.0000000
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Polars for RAF 30 MOD AIRFOIL (raf30md-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| raf30md-il | 50,000 | 9 | 26.4 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf30md-il | 50,000 | 5 | 25.1 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf30md-il | 100,000 | 9 | 35.2 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf30md-il | 100,000 | 5 | 31 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf30md-il | 200,000 | 9 | 42.7 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf30md-il | 200,000 | 5 | 36.3 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf30md-il | 500,000 | 9 | 47.9 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf30md-il | 500,000 | 5 | 52.3 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf30md-il | 1,000,000 | 9 | 59.9 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf30md-il | 1,000,000 | 5 | 65.4 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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