USA 51 AIRFOIL (usa51-il)
USA 51 AIRFOIL - USA-51 airfoil
| Details | Dat file | Parser | |
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(usa51-il) USA 51 AIRFOIL USA-51 airfoil Max thickness 9.3% at 30% chord. Max camber 2.6% at 30% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
USA 51 AIRFOIL
17. 17.
0.0000000 0.0000000
0.0125000 0.0157000
0.0250000 0.0240000
0.0500000 0.0390000
0.0750000 0.0480000
0.1000000 0.0536000
0.1500000 0.0626000
0.2000000 0.0687000
0.3000000 0.0723000
0.4000000 0.0687000
0.5000000 0.0630000
0.6000000 0.0547000
0.7000000 0.0437000
0.8000000 0.0317000
0.9000000 0.0178000
0.9500000 0.0090000
1.0000000 0.0000000
0.0000000 0.0000000
0.0125000 -.0087000
0.0250000 -.0117000
0.0500000 -.0157000
0.0750000 -.0180000
0.1000000 -.0193000
0.1500000 -.0207000
0.2000000 -.0210000
0.3000000 -.0210000
0.4000000 -.0200000
0.5000000 -.0183000
0.6000000 -.0160000
0.7000000 -.0123000
0.8000000 -.0083000
0.9000000 -.0043000
0.9500000 -.0025000
1.0000000 0.0000000
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Polars for USA 51 AIRFOIL (usa51-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| usa51-il | 50,000 | 9 | 32.4 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa51-il | 50,000 | 5 | 35.2 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa51-il | 100,000 | 9 | 48.2 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa51-il | 100,000 | 5 | 48.9 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa51-il | 200,000 | 9 | 63.2 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa51-il | 200,000 | 5 | 60.3 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa51-il | 500,000 | 9 | 80.7 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa51-il | 500,000 | 5 | 73 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa51-il | 1,000,000 | 9 | 92.1 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa51-il | 1,000,000 | 5 | 86.2 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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