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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(hq17-il) HORSTMANN AND QUAST HQ-17/14.38 AIRFOIL (MEASURED) | Airfoil measured from an ASW22 wing Max thickness 15.2% at 42% chord Max camber 4.5% at 42% chord | Remove Airfoil details Airfoil plotter |
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Polars for (hq17-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| hq17-il | 50,000 | 9 | 22.5 at α=12.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq17-il | 50,000 | 5 | 18.3 at α=12.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq17-il | 100,000 | 9 | 34.2 at α=11.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq17-il | 100,000 | 5 | 32.5 at α=10.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq17-il | 200,000 | 9 | 68.9 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq17-il | 200,000 | 5 | 66.5 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq17-il | 500,000 | 9 | 113.5 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq17-il | 500,000 | 5 | 103.3 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq17-il | 1,000,000 | 9 | 139.5 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq17-il | 1,000,000 | 5 | 122.5 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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