Airfoil Comparison
Select airfoils from the airfoil database or add your own airfoils and compare the airfoil shape and lift/drag polars.
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(bacnlf-il) BOEING HSNLF AIRFOIL | Boeing high speed natural laminar flow airfoil from a European patent (EP 0111785A1) Max thickness 10.1% at 43.7% chord Max camber 1.3% at 76.7% chord | Remove Airfoil details Airfoil plotter |
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Polars for (bacnlf-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| bacnlf-il | 50,000 | 9 | 26.1 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| bacnlf-il | 50,000 | 5 | 28.3 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| bacnlf-il | 100,000 | 9 | 35.6 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| bacnlf-il | 100,000 | 5 | 40.4 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| bacnlf-il | 200,000 | 9 | 55.8 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| bacnlf-il | 200,000 | 5 | 53 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| bacnlf-il | 500,000 | 9 | 78.4 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| bacnlf-il | 500,000 | 5 | 64.9 at α=2° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| bacnlf-il | 1,000,000 | 9 | 88.3 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| bacnlf-il | 1,000,000 | 5 | 66.1 at α=1° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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