USA 31 AIRFOIL (usa31-il)
USA 31 AIRFOIL - USA-31 airfoil
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(usa31-il) USA 31 AIRFOIL USA-31 airfoil Max thickness 14.8% at 19.7% chord. Max camber 9.3% at 39.7% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
USA 31 AIRFOIL
17. 17.
0.0000000 0.0000000
0.0118100 0.0342200
0.0240000 0.0514400
0.0485600 0.0758800
0.0732700 0.0923200
0.0980200 0.1057700
0.1476700 0.1256700
0.1974200 0.1395600
0.2971700 0.1543600
0.3971400 0.1561600
0.4972800 0.1489600
0.5975600 0.1337700
0.6979500 0.1125700
0.7984900 0.0833700
0.8991800 0.0451900
0.9496200 0.0211000
1.0000000 0.0000000
0.0000000 0.0000000
0.0126900 -.0147700
0.0252200 -.0165500
0.0502500 -.0181000
0.0752700 -.0186500
0.1002500 -.0182000
0.1501300 -.0144000
0.2005900 -.0085400
0.2999200 0.0122800
0.3993900 0.0311900
0.4994200 0.0299900
0.5995200 0.0248000
0.6996601 0.0176000
0.7998200 0.0094000
0.8999500 0.0022000
0.9500100 -.0009000
1.0000000 0.0000000
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Polars for USA 31 AIRFOIL (usa31-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| usa31-il | 50,000 | 9 | 4.9 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa31-il | 50,000 | 5 | 14.1 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa31-il | 100,000 | 9 | 34.9 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa31-il | 100,000 | 5 | 40.8 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa31-il | 200,000 | 9 | 62.3 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa31-il | 200,000 | 5 | 54.8 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa31-il | 500,000 | 9 | 76.8 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa31-il | 500,000 | 5 | 69.2 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa31-il | 1,000,000 | 9 | 88.2 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa31-il | 1,000,000 | 5 | 79.9 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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