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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(hq308-il) HQ 3.0/8 AIRFOIL | Quabeck HQ 3.0/8 R/C sailplane airfoil Max thickness 8% at 35% chord Max camber 3% at 50% chord | Remove Airfoil details Airfoil plotter |
(isa961-il) I.S.A. 961 | I.S.A. 961 airfoil Max thickness 9.3% at 20% chord Max camber 4.6% at 40% chord | Remove Airfoil details Airfoil plotter |
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Polars for (hq308-il,isa961-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| hq308-il | 50,000 | 9 | 40.6 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq308-il | 50,000 | 5 | 42.2 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq308-il | 100,000 | 9 | 62.5 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq308-il | 100,000 | 5 | 60.9 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq308-il | 200,000 | 9 | 86.1 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq308-il | 200,000 | 5 | 79.6 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq308-il | 500,000 | 9 | 116.5 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq308-il | 500,000 | 5 | 99.5 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq308-il | 1,000,000 | 9 | 135.4 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq308-il | 1,000,000 | 5 | 99.9 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| isa961-il | 50,000 | 9 | 34.9 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| isa961-il | 50,000 | 5 | 39.5 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| isa961-il | 100,000 | 9 | 55.5 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| isa961-il | 100,000 | 5 | 53.9 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| isa961-il | 200,000 | 9 | 70.4 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| isa961-il | 200,000 | 5 | 63 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| isa961-il | 500,000 | 9 | 80 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| isa961-il | 500,000 | 5 | 75.5 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| isa961-il | 1,000,000 | 9 | 90.6 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| isa961-il | 1,000,000 | 5 | 88.9 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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