BOEING 106 AIRFOIL (boe106-il)
BOEING 106 AIRFOIL - Boeing 106 airfoil
| Details | Dat file | Parser | |
|
(boe106-il) BOEING 106 AIRFOIL Boeing 106 airfoil Max thickness 13.1% at 30% chord. Max camber 3.3% at 40% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
BOEING 106 AIRFOIL
17. 17.
0.0000000 0.0000000
0.0100000 0.0213800
0.0250000 0.0348000
0.0500000 0.0490000
0.0750000 0.0594000
0.1000000 0.0676000
0.1500000 0.0801500
0.2000000 0.0895600
0.3000000 0.0979400
0.4000000 0.0975200
0.5000000 0.0905000
0.6000000 0.0788800
0.7000000 0.0628600
0.8000000 0.0436400
0.9000000 0.0224200
0.9500000 0.0114100
1.0000000 0.0004000
0.0000000 0.0000000
0.0125000 -.0141000
0.0250000 -.0191000
0.0500000 -.0243000
0.0750000 -.0277000
0.1000000 -.0296000
0.1500000 -.0315300
0.2000000 -.0328400
0.3000000 -.0326600
0.4000000 -.0306800
0.5000000 -.0279000
0.6000000 -.0241200
0.7000000 -.0187400
0.8000000 -.0131600
0.9000000 -.0071800
0.9500000 -.0037900
1.0000000 0.0000000
|
No parser warnings |
Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file |
Similar airfoils
|
Polars for BOEING 106 AIRFOIL (boe106-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| boe106-il | 50,000 | 9 | 29.7 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| boe106-il | 50,000 | 5 | 32.5 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| boe106-il | 100,000 | 9 | 51.6 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| boe106-il | 100,000 | 5 | 52.8 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| boe106-il | 200,000 | 9 | 72.1 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| boe106-il | 200,000 | 5 | 70.2 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| boe106-il | 500,000 | 9 | 98.8 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| boe106-il | 500,000 | 5 | 92 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| boe106-il | 1,000,000 | 9 | 118.8 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| boe106-il | 1,000,000 | 5 | 108.2 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||