USA 50 AIRFOIL (usa50-il)
USA 50 AIRFOIL - USA-50 airfoil
| Details | Dat file | Parser | |
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(usa50-il) USA 50 AIRFOIL USA-50 airfoil Max thickness 7% at 30% chord. Max camber 2% at 40% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
USA 50 AIRFOIL
17. 17.
0.0000000 0.0000000
0.0125000 0.0100000
0.0250000 0.0163000
0.0500000 0.0247000
0.0750000 0.0307000
0.1000000 0.0360000
0.1500000 0.0440000
0.2000000 0.0490000
0.3000000 0.0537000
0.4000000 0.0540000
0.5000000 0.0494000
0.6000000 0.0440000
0.7000000 0.0367000
0.8000000 0.0280000
0.9000000 0.0167000
0.9500000 0.0100000
1.0000000 0.0000000
0.0000000 0.0000000
0.0125000 -.0067000
0.0250000 -.0097000
0.0500000 -.0123000
0.0750000 -.0133000
0.1000000 -.0143000
0.1500000 -.0157000
0.2000000 -.0167000
0.3000000 -.0167000
0.4000000 -.0150000
0.5000000 -.0130000
0.6000000 -.0107000
0.7000000 -.0083000
0.8000000 -.0063000
0.9000000 -.0040000
0.9500000 -.0027000
1.0000000 0.0000000
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Polars for USA 50 AIRFOIL (usa50-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| usa50-il | 50,000 | 9 | 36.4 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa50-il | 50,000 | 5 | 36.1 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa50-il | 100,000 | 9 | 51.1 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa50-il | 100,000 | 5 | 49.2 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa50-il | 200,000 | 9 | 65.1 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa50-il | 200,000 | 5 | 60.5 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa50-il | 500,000 | 9 | 80.4 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa50-il | 500,000 | 5 | 73.3 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa50-il | 1,000,000 | 9 | 92.3 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa50-il | 1,000,000 | 5 | 83.7 at α=2° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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