RAF-48 AIRFOIL (raf48-il)
RAF-48 AIRFOIL - RAF-48 airfoil
| Details | Dat file | Parser | |
|
(raf48-il) RAF-48 AIRFOIL RAF-48 airfoil Max thickness 15% at 30% chord. Max camber 2.9% at 40% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
RAF-48 AIRFOIL
17. 17.
0.000000 0.000000
0.012500 0.026000
0.025000 0.036500
0.050000 0.052000
0.075000 0.063900
0.100000 0.073000
0.150000 0.086300
0.200000 0.095300
0.300000 0.104000
0.400000 0.102000
0.500000 0.093800
0.600000 0.079400
0.700000 0.060500
0.800000 0.040200
0.900000 0.019500
0.950000 0.010050
1.000000 0.000000
0.000000 0.000000
0.012500 -0.016500
0.025000 -0.023400
0.050000 -0.031600
0.075000 -0.036900
0.100000 -0.040300
0.150000 -0.044100
0.200000 -0.045800
0.300000 -0.045600
0.400000 -0.043300
0.500000 -0.039000
0.600000 -0.033600
0.700000 -0.026500
0.800000 -0.018300
0.900000 -0.010000
0.950000 -0.006400
1.000000 0.000000
|
No parser warnings |
Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file |
Similar airfoils
|
Polars for RAF-48 AIRFOIL (raf48-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| raf48-il | 50,000 | 9 | 7.4 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf48-il | 50,000 | 5 | 25.8 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf48-il | 100,000 | 9 | 45.6 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf48-il | 100,000 | 5 | 49.2 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf48-il | 200,000 | 9 | 68.5 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf48-il | 200,000 | 5 | 67.8 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf48-il | 500,000 | 9 | 97.8 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf48-il | 500,000 | 5 | 93.7 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf48-il | 1,000,000 | 9 | 121.8 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf48-il | 1,000,000 | 5 | 108.1 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||