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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(hobiesm-il) HOBIESMO1.DAT | Hobie Hawk airfoil (Hobie Hawk R/C sailplane) Max thickness 8.6% at 25% chord Max camber 3.8% at 45% chord | Remove Airfoil details Airfoil plotter |
(hq158-il) HQ 1.5/8 AIRFOIL | Quabeck HQ 1.5/8 R/C sailplane airfoil Max thickness 8% at 32.5% chord Max camber 1.5% at 50% chord | Remove Airfoil details Airfoil plotter |
(hq109-il) HQ 1.0/9 AIRFOIL | Quabeck HQ 1.0/9 R/C sailplane airfoil Max thickness 9% at 35% chord Max camber 1% at 50% chord | Remove Airfoil details Airfoil plotter |
(hq010-il) HQ 0/10 AIRFOIL | Quabeck HQ 0/10 R/C sailplane airfoil Max thickness 10% at 33.9% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
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Polars for (hobiesm-il,hq158-il,hq109-il,hq010-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| hobiesm-il | 50,000 | 9 | 41.7 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hobiesm-il | 50,000 | 5 | 41.5 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hobiesm-il | 100,000 | 9 | 60.9 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hobiesm-il | 100,000 | 5 | 60.4 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hobiesm-il | 200,000 | 9 | 81.5 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hobiesm-il | 200,000 | 5 | 79 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hobiesm-il | 500,000 | 9 | 110 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hobiesm-il | 500,000 | 5 | 101.9 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hobiesm-il | 1,000,000 | 9 | 130.7 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hobiesm-il | 1,000,000 | 5 | 118.2 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq158-il | 50,000 | 9 | 35.7 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq158-il | 50,000 | 5 | 35.9 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq158-il | 100,000 | 9 | 51.9 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq158-il | 100,000 | 5 | 49 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq158-il | 200,000 | 9 | 68.3 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq158-il | 200,000 | 5 | 60.7 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq158-il | 500,000 | 9 | 86.8 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq158-il | 500,000 | 5 | 70 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq158-il | 1,000,000 | 9 | 92 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq158-il | 1,000,000 | 5 | 77.5 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq109-il | 50,000 | 9 | 32.8 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq109-il | 50,000 | 5 | 33.1 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq109-il | 100,000 | 9 | 48 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq109-il | 100,000 | 5 | 45 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq109-il | 200,000 | 9 | 62.9 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq109-il | 200,000 | 5 | 55.3 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq109-il | 500,000 | 9 | 79.5 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq109-il | 500,000 | 5 | 66.1 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq109-il | 1,000,000 | 9 | 82.8 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq109-il | 1,000,000 | 5 | 75.6 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq010-il | 50,000 | 9 | 28 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq010-il | 50,000 | 5 | 27.3 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq010-il | 100,000 | 9 | 39.7 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq010-il | 100,000 | 5 | 36 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq010-il | 200,000 | 9 | 50.1 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq010-il | 200,000 | 5 | 41.4 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq010-il | 500,000 | 9 | 54.6 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq010-il | 500,000 | 5 | 56.9 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq010-il | 1,000,000 | 9 | 71 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq010-il | 1,000,000 | 5 | 70.7 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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