Davis AIRFOIL (davis-il)
Davis AIRFOIL - Consolidated/Davis airfoil (B-24 wing?)
| Details | Dat file | Parser | |
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(davis-il) Davis AIRFOIL Consolidated/Davis airfoil (B-24 wing?) Max thickness 11.3% at 30% chord. Max camber 3.7% at 40% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
Davis AIRFOIL
17. 17.
0.0000000 0.0000000
0.0125000 0.0175000
0.0250000 0.0268000
0.0500000 0.0405000
0.0750000 0.0510000
0.1000000 0.0600000
0.1500000 0.0740000
0.2000000 0.0825000
0.2500000 0.0875000
0.3000000 0.0900000
0.4000000 0.0915000
0.5000000 0.0860000
0.6000000 0.0770000
0.7000000 0.0625000
0.8000000 0.0460000
0.9000000 0.0250000
1.0000000 0.0000000
0.0000000 0.0000000
0.0125000 -.0105000
0.0250000 -.0147000
0.0500000 -.0205000
0.0750000 -.0240000
0.1000000 -.0260000
0.1500000 -.0270000
0.2000000 -.0265000
0.2500000 -.0245000
0.3000000 -.0225000
0.4000000 -.0176500
0.5000000 -.0130000
0.6000000 -.0100000
0.7000000 -.0075000
0.8000000 -.0045000
0.9000000 -.0020000
1.0000000 0.0000000
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Polars for Davis AIRFOIL (davis-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| davis-il | 50,000 | 9 | 22.2 at α=11° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| davis-il | 50,000 | 5 | 36.4 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| davis-il | 100,000 | 9 | 54 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| davis-il | 100,000 | 5 | 55 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| davis-il | 200,000 | 9 | 76.1 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| davis-il | 200,000 | 5 | 72.1 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| davis-il | 500,000 | 9 | 101.4 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| davis-il | 500,000 | 5 | 91.3 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| davis-il | 1,000,000 | 9 | 120.8 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| davis-il | 1,000,000 | 5 | 107 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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