FX 60-100 (126) AIRFOIL (fx601001-il)
FX 60-100 (126) AIRFOIL - Wortmann FX 60-100 (126) airfoil
| Details | Dat file | Parser | |
|
(fx601001-il) FX 60-100 (126) AIRFOIL Wortmann FX 60-100 (126) airfoil Max thickness 10.1% at 30.8% chord. Max camber 3.6% at 59.7% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
FX 60-100 (126) AIRFOIL
18. 18.
0.0000000 0.0000000
0.0096000 0.0146000
0.0260000 0.0262000
0.0516000 0.0385000
0.0842000 0.0498000
0.1030000 0.0550000
0.1460000 0.0636000
0.1960000 0.0706000
0.2500000 0.0755000
0.3080000 0.0784000
0.4420000 0.0779000
0.5000000 0.0742000
0.5970000 0.0655000
0.6910000 0.0543000
0.8040000 0.0370000
0.8960000 0.0208000
0.9480000 0.0105000
1.0000000 0.0000000
0.0000000 0.0000000
0.0096000 -.0075000
0.0260000 -.0134000
0.0516000 -.0178000
0.0842000 -.0213000
0.1030000 -.0228000
0.1460000 -.0248000
0.1960000 -.0255000
0.2500000 -.0246000
0.3080000 -.0228000
0.4420000 -.0115000
0.5000000 -.0035000
0.5970000 0.0060000
0.6910000 0.0125000
0.8040000 0.0150000
0.8960000 0.0105000
0.9480000 0.0066000
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 FX 60-100 (126) AIRFOIL (fx601001-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| fx601001-il | 50,000 | 9 | 38.3 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx601001-il | 50,000 | 5 | 42.5 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx601001-il | 100,000 | 9 | 61 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx601001-il | 100,000 | 5 | 62.5 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx601001-il | 200,000 | 9 | 84.2 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx601001-il | 200,000 | 5 | 76.8 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx601001-il | 500,000 | 9 | 103 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx601001-il | 500,000 | 5 | 92.4 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx601001-il | 1,000,000 | 9 | 116.1 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx601001-il | 1,000,000 | 5 | 101.4 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||