RAF 6 AIRFOIL (raf6-il)
RAF 6 AIRFOIL - RAF-6 airfoil
| Details | Dat file | Parser | |
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(raf6-il) RAF 6 AIRFOIL RAF-6 airfoil Max thickness 10% at 30% chord. Max camber 4.6% at 30% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
RAF 6 AIRFOIL
13. 13.
0.0000000 0.0000000
0.0248700 0.0359900
0.0498100 0.0540800
0.0997300 0.0742600
0.1996700 0.0906200
0.2996600 0.0957800
0.3996600 0.0953400
0.4996700 0.0917000
0.5997000 0.0840600
0.6997400 0.0714200
0.7998101 0.0537800
0.8998800 0.0331400
1.0000000 0.0015000
0.0000000 0.0000000
0.0250200 -.0050100
0.0500200 -.0049200
0.1000200 -.0047400
0.2000200 -.0043800
0.3000100 -.0040200
0.4000100 -.0036600
0.5000100 -.0033000
0.6000100 -.0029400
0.7000100 -.0025800
0.8000100 -.0022200
0.9000100 -.0018600
1.0000000 -.0015000
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Similar airfoils
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Polars for RAF 6 AIRFOIL (raf6-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| raf6-il | 50,000 | 9 | 35.7 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf6-il | 50,000 | 5 | 36.7 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf6-il | 100,000 | 9 | 51.9 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf6-il | 100,000 | 5 | 52.5 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf6-il | 200,000 | 9 | 70.3 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf6-il | 200,000 | 5 | 68.2 at α=1.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf6-il | 500,000 | 9 | 90.5 at α=0.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf6-il | 500,000 | 5 | 85 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf6-il | 1,000,000 | 9 | 104.8 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf6-il | 1,000,000 | 5 | 105 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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