RAF 27 AIRFOIL (raf27-il)
RAF 27 AIRFOIL - RAF-27 airfoil
| Details | Dat file | Parser | |
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(raf27-il) RAF 27 AIRFOIL RAF-27 airfoil Max thickness 9.8% 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 27 AIRFOIL
17. 17.
0.0000000 0.0000000
0.0125000 0.0134000
0.0250000 0.0190000
0.0500000 0.0267000
0.0750000 0.0320000
0.1000000 0.0362000
0.1500000 0.0424000
0.2000000 0.0460000
0.3000000 0.0488000
0.4000000 0.0478000
0.5000000 0.0437000
0.6000000 0.0377000
0.7000000 0.0296000
0.8000000 0.0208000
0.9000000 0.0112000
0.9500000 0.0061000
1.0000000 0.0000000
0.0000000 0.0000000
0.0125000 -.0134000
0.0250000 -.0190000
0.0500000 -.0267000
0.0750000 -.0320000
0.1000000 -.0362000
0.1500000 -.0424000
0.2000000 -.0460000
0.3000000 -.0488000
0.4000000 -.0478000
0.5000000 -.0437000
0.6000000 -.0377000
0.7000000 -.0296000
0.8000000 -.0208000
0.9000000 -.0112000
0.9500000 -.0061000
1.0000000 0.0000000
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Polars for RAF 27 AIRFOIL (raf27-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| raf27-il | 50,000 | 9 | 28.3 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf27-il | 50,000 | 5 | 27.5 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf27-il | 100,000 | 9 | 39.5 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf27-il | 100,000 | 5 | 36.5 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf27-il | 200,000 | 9 | 49.1 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf27-il | 200,000 | 5 | 43.9 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf27-il | 500,000 | 9 | 56.8 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf27-il | 500,000 | 5 | 58.4 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf27-il | 1,000,000 | 9 | 69.4 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf27-il | 1,000,000 | 5 | 71.5 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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