USA 48 AIRFOIL (usa48-il)
USA 48 AIRFOIL - USA-48 airfoil
| Details | Dat file | Parser | |
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(usa48-il) USA 48 AIRFOIL USA-48 airfoil Max thickness 14.9% 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 |
USA 48 AIRFOIL
17. 17.
0.0000000 0.0000000
0.0125000 0.0220000
0.0250000 0.0320000
0.0500000 0.0480000
0.0750000 0.0610000
0.1000000 0.0690000
0.1500000 0.0828000
0.2000000 0.0922000
0.3000000 0.1010000
0.4000000 0.1015000
0.5000000 0.0948000
0.6000000 0.0836000
0.7000000 0.0683000
0.8000000 0.0507000
0.9000000 0.0287000
0.9500000 0.0160000
1.0000000 0.0000000
0.0000000 0.0000000
0.0125000 -.0140000
0.0250000 -.0200000
0.0500000 -.0270000
0.0750000 -.0343000
0.1000000 -.0383000
0.1500000 -.0453000
0.2000000 -.0480000
0.3000000 -.0480000
0.4000000 -.0440000
0.5000000 -.0390000
0.6000000 -.0320000
0.7000000 -.0197000
0.8000000 -.0110000
0.9000000 -.0057000
0.9500000 -.0027000
1.0000000 0.0000000
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Polars for USA 48 AIRFOIL (usa48-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| usa48-il | 50,000 | 9 | 24.1 at α=12° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa48-il | 50,000 | 5 | 30.6 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa48-il | 100,000 | 9 | 49.8 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa48-il | 100,000 | 5 | 49.3 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa48-il | 200,000 | 9 | 69.1 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa48-il | 200,000 | 5 | 63.2 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa48-il | 500,000 | 9 | 85.1 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa48-il | 500,000 | 5 | 65.1 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa48-il | 1,000,000 | 9 | 81.4 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa48-il | 1,000,000 | 5 | 73.2 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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