USA 49 AIRFOIL (usa49-il)
USA 49 AIRFOIL - USA-49 airfoil
| Details | Dat file | Parser | |
|
(usa49-il) USA 49 AIRFOIL USA-49 airfoil Max thickness 7.3% at 30% chord. Max camber 1.7% at 30% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
USA 49 AIRFOIL
17. 17.
0.0000000 0.0000000
0.0125000 0.0140000
0.0250000 0.0200000
0.0500000 0.0267000
0.0750000 0.0330000
0.1000000 0.0386000
0.1500000 0.0457000
0.2000000 0.0500000
0.3000000 0.0535000
0.4000000 0.0527000
0.5000000 0.0483000
0.6000000 0.0424000
0.7000000 0.0350000
0.8000000 0.0260000
0.9000000 0.0150000
0.9500000 0.0090000
1.0000000 0.0035000
0.0000000 0.0000000
0.0125000 -.0065000
0.0250000 -.0097000
0.0500000 -.0140000
0.0750000 -.0163000
0.1000000 -.0173000
0.1500000 -.0183000
0.2000000 -.0190000
0.3000000 -.0190000
0.4000000 -.0180000
0.5000000 -.0167000
0.6000000 -.0143000
0.7000000 -.0110000
0.8000000 -.0077000
0.9000000 -.0030000
0.9500000 -.0010000
1.0000000 0.0012000
|
No parser warnings |
Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file |
Similar airfoils
|
Polars for USA 49 AIRFOIL (usa49-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| usa49-il | 50,000 | 9 | 33.1 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa49-il | 50,000 | 5 | 33.6 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa49-il | 100,000 | 9 | 43.9 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa49-il | 100,000 | 5 | 42.1 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa49-il | 200,000 | 9 | 52.1 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa49-il | 200,000 | 5 | 48.5 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa49-il | 500,000 | 9 | 59.7 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa49-il | 500,000 | 5 | 65.6 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa49-il | 1,000,000 | 9 | 78 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa49-il | 1,000,000 | 5 | 75.1 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||