USA 29 AIRFOIL (usa29-il)
USA 29 AIRFOIL - USA-29 airfoil
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(usa29-il) USA 29 AIRFOIL USA-29 airfoil Max thickness 13.2% at 29.7% chord. Max camber 5.5% at 39.7% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
USA 29 AIRFOIL
17. 17.
0.0000000 0.0000000
0.0120100 0.0178300
0.0242400 0.0274700
0.0487800 0.0441500
0.0734000 0.0580300
0.0980800 0.0695100
0.1475900 0.0874700
0.1972300 0.1003400
0.2968500 0.1140900
0.3968200 0.1152500
0.4970300 0.1075200
0.5974100 0.0937900
0.6978800 0.0767600
0.7985000 0.0544400
0.8992100 0.0286200
0.9496100 0.0142100
1.0000000 0.0000000
0.0000000 0.0000000
0.0129600 -.0166400
0.0256200 -.0224900
0.0507400 -.0269000
0.0758300 -.0299100
0.1008400 -.0305200
0.1508400 -.0303400
0.2007600 -.0273600
0.3004800 -.0175100
0.4001100 -.0041600
0.5000700 -.0026000
0.6001400 -.0049400
0.7002700 -.0096700
0.8003200 -.0116100
0.9002500 -.0090500
0.9501700 -.0062800
1.0000000 0.0000000
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Polars for USA 29 AIRFOIL (usa29-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| usa29-il | 50,000 | 9 | 6.6 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa29-il | 50,000 | 5 | 27.1 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa29-il | 100,000 | 9 | 50.4 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa29-il | 100,000 | 5 | 52.4 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa29-il | 200,000 | 9 | 74.6 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa29-il | 200,000 | 5 | 72.6 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa29-il | 500,000 | 9 | 90 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa29-il | 500,000 | 5 | 80.7 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa29-il | 1,000,000 | 9 | 101.1 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa29-il | 1,000,000 | 5 | 95.5 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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