USA 40 AIRFOIL (usa40-il)
USA 40 AIRFOIL - USA-40 airfoil
| Details | Dat file | Parser | |
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(usa40-il) USA 40 AIRFOIL USA-40 airfoil Max thickness 13.3% at 30% chord. Max camber 4.2% at 40% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
USA 40 AIRFOIL
17. 17.
0.0000000 0.0000000
0.0125100 0.0263000
0.0250100 0.0360000
0.0500100 0.0562900
0.0750100 0.0686900
0.1000200 0.0789800
0.1500200 0.0935700
0.2000200 0.1019600
0.3000200 0.1071400
0.4000200 0.1035200
0.5000200 0.0949000
0.6000200 0.0815800
0.7000100 0.0655600
0.8000100 0.0465400
0.9000100 0.0251200
0.9500000 0.0135100
1.0000000 0.0005000
0.0000000 0.0000000
0.0125000 -.0190000
0.0250000 -.0240100
0.0499900 -.0287100
0.0749900 -.0307200
0.0999900 -.0320200
0.1499900 -.0326300
0.1999900 -.0307400
0.2999900 -.0260600
0.4000000 -.0196800
0.5000000 -.0131000
0.6000000 -.0058200
0.7000000 0.0018600
0.8000000 0.0075400
0.9000000 0.0065200
0.9500000 0.0031100
1.0000000 -.0005000
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Polars for USA 40 AIRFOIL (usa40-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| usa40-il | 50,000 | 9 | 23.3 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa40-il | 50,000 | 5 | 35.3 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa40-il | 100,000 | 9 | 50.1 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa40-il | 100,000 | 5 | 53.2 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa40-il | 200,000 | 9 | 71.1 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa40-il | 200,000 | 5 | 69.2 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa40-il | 500,000 | 9 | 95.4 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa40-il | 500,000 | 5 | 82.2 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa40-il | 1,000,000 | 9 | 105.1 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa40-il | 1,000,000 | 5 | 87 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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