RAF 32 MOD AIRFOIL (raf32md-il)
RAF 32 MOD AIRFOIL - RAF-32 MOD airfoil
| Details | Dat file | Parser | |
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(raf32md-il) RAF 32 MOD AIRFOIL RAF-32 MOD airfoil Max thickness 10.2% at 30% chord. Max camber 4% at 50% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
RAF 32 MOD AIRFOIL
15. 15.
0.0000000 0.0000000
0.0125000 0.0174300
0.0250000 0.0254600
0.0500000 0.0366200
0.1000000 0.0530400
0.1500000 0.0645600
0.2000000 0.0733800
0.3000000 0.0845200
0.4000000 0.0881600
0.5000000 0.0853000
0.6000000 0.0769400
0.7000000 0.0638800
0.8000000 0.0462200
0.9000000 0.0251600
1.0000000 0.0000000
0.0000000 0.0000000
0.0125000 -.0113700
0.0250000 -.0147400
0.0500000 -.0190800
0.1000000 -.0223600
0.1500000 -.0228400
0.2000000 -.0221200
0.3000000 -.0170800
0.4000000 -.0112400
0.5000000 -.0062000
0.6000000 0.0001400
0.7000000 0.0038800
0.8000000 0.0054200
0.9000000 0.0037600
1.0000000 0.0000000
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Polars for RAF 32 MOD AIRFOIL (raf32md-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| raf32md-il | 50,000 | 9 | 38 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf32md-il | 50,000 | 5 | 37.5 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf32md-il | 100,000 | 9 | 62.1 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf32md-il | 100,000 | 5 | 61.3 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf32md-il | 200,000 | 9 | 87.2 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf32md-il | 200,000 | 5 | 83.8 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf32md-il | 500,000 | 9 | 120.8 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf32md-il | 500,000 | 5 | 110.5 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf32md-il | 1,000,000 | 9 | 144.4 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf32md-il | 1,000,000 | 5 | 124.3 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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