RAF 31 AIRFOIL (raf31-il)
RAF 31 AIRFOIL - RAF-31 airfoil
| Details | Dat file | Parser | |
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(raf31-il) RAF 31 AIRFOIL RAF-31 airfoil Max thickness 12.7% at 30% chord. Max camber 2.1% at 50% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
RAF 31 AIRFOIL
18. 18.
0.0000000 0.0000000
0.0125000 0.0178800
0.0250000 0.0269700
0.0500000 0.0387300
0.0750000 0.0470000
0.1000000 0.0536600
0.1500000 0.0644900
0.2000000 0.0723200
0.2500000 0.0768500
0.3000000 0.0807800
0.4000000 0.0812400
0.5000000 0.0777000
0.6000000 0.0685600
0.7000000 0.0550200
0.8000000 0.0386800
0.9000000 0.0200400
0.9500000 0.0113700
1.0000000 0.0000000
0.0000000 0.0000000
0.0125000 -.0173200
0.0250000 -.0228300
0.0500000 -.0308700
0.0750000 -.0355000
0.1000000 -.0389400
0.1500000 -.0440100
0.2000000 -.0462800
0.2500000 -.0471500
0.3000000 -.0466200
0.4000000 -.0423600
0.5000000 -.0363000
0.6000000 -.0284400
0.7000000 -.0201800
0.8000000 -.0121200
0.9000000 -.0058600
0.9500000 -.0033300
1.0000000 0.0000000
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Polars for RAF 31 AIRFOIL (raf31-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| raf31-il | 50,000 | 9 | 33.8 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf31-il | 50,000 | 5 | 33.5 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf31-il | 100,000 | 9 | 53 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf31-il | 100,000 | 5 | 50.3 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf31-il | 200,000 | 9 | 72.1 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf31-il | 200,000 | 5 | 65 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf31-il | 500,000 | 9 | 93.3 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf31-il | 500,000 | 5 | 79.6 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf31-il | 1,000,000 | 9 | 106.3 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf31-il | 1,000,000 | 5 | 83.3 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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