USA 35 AIRFOIL (usa35-il)
USA 35 AIRFOIL - USA-35 airfoil
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(usa35-il) USA 35 AIRFOIL USA-35 airfoil Max thickness 18.2% at 29.4% chord. Max camber 6.4% at 39.4% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
USA 35 AIRFOIL
17. 17.
0.0000000 0.0000000
0.0109300 0.0380500
0.0228000 0.0534400
0.0468400 0.0769300
0.0710700 0.0954200
0.0955000 0.1094300
0.1447100 0.1286500
0.1941600 0.1418900
0.2937000 0.1530900
0.3937700 0.1515000
0.4943000 0.1386400
0.5950500 0.1202900
0.6960300 0.0965400
0.7971900 0.0683000
0.8984800 0.0369700
0.9491900 0.0196600
1.0000000 0.0021500
0.0000000 0.0000000
0.0135900 -.0265400
0.0263500 -.0327200
0.0515200 -.0369800
0.0765600 -.0379500
0.1015700 -.0381200
0.1515300 -.0370600
0.2014200 -.0344100
0.3011700 -.0284100
0.4009200 -.0224000
0.5006900 -.0167000
0.6004900 -.0118900
0.7003300 -.0079800
0.8002000 -.0048700
0.9001300 -.0030600
0.9500901 -.0023000
1.0000000 -.0021500
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Polars for USA 35 AIRFOIL (usa35-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| usa35-il | 50,000 | 9 | 4.3 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa35-il | 50,000 | 5 | 20.6 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa35-il | 100,000 | 9 | 35.4 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa35-il | 100,000 | 5 | 46.4 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa35-il | 200,000 | 9 | 66.5 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa35-il | 200,000 | 5 | 67 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa35-il | 500,000 | 9 | 97.7 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa35-il | 500,000 | 5 | 92.2 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa35-il | 1,000,000 | 9 | 122.3 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa35-il | 1,000,000 | 5 | 109.5 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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