RAF 38 AIRFOIL (raf38-il)
RAF 38 AIRFOIL - RAF-38 airfoil
| Details | Dat file | Parser | |
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(raf38-il) RAF 38 AIRFOIL RAF-38 airfoil Max thickness 12.7% at 30% chord. Max camber 2.5% at 40% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
RAF 38 AIRFOIL
13. 13.
0.0000000 0.0000000
0.0250000 0.0298000
0.0500000 0.0421000
0.1000000 0.0594000
0.2000000 0.0791000
0.3000000 0.0875000
0.4000000 0.0869000
0.5000000 0.0806000
0.6000000 0.0685000
0.7000000 0.0527000
0.8000000 0.0354000
0.9000000 0.0183000
1.0000000 0.0000000
0.0000000 0.0000000
0.0250000 -.0202000
0.0500000 -.0266000
0.1000000 -.0338000
0.2000000 -.0386000
0.3000000 -.0390000
0.4000000 -.0366000
0.5000000 -.0323000
0.6000000 -.0273000
0.7000000 -.0213000
0.8000000 -.0146000
0.9000000 -.0079000
1.0000000 0.0000000
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Polars for RAF 38 AIRFOIL (raf38-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| raf38-il | 50,000 | 9 | 31.6 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf38-il | 50,000 | 5 | 32.5 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf38-il | 100,000 | 9 | 51.6 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf38-il | 100,000 | 5 | 51.9 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf38-il | 200,000 | 9 | 71.5 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf38-il | 200,000 | 5 | 69 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf38-il | 500,000 | 9 | 96.6 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf38-il | 500,000 | 5 | 90.5 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf38-il | 1,000,000 | 9 | 114.7 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf38-il | 1,000,000 | 5 | 98.9 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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