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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(hq2510-il) HQ 2.5/10 AIRFOIL | Quabeck HQ 2.5/10 R/C sailplane airfoil Max thickness 10% at 35% chord Max camber 2.5% at 50% chord | Remove Airfoil details Airfoil plotter |
(cp-180-050-gn) Cambered plate C=18% T=5% R=0.78 | HAWT pipe blade with coordinates based on top surface. Camber=18% Wall thickness=5% Radius=0.784 Max thickness 5% at 3.2% chord Max camber 16.4% at 49.3% chord | Remove Airfoil details Airfoil plotter |
(naca65209-il) NACA 65-209 | NACA 65-209 airfoil Max thickness 9% at 40% chord Max camber 1.1% at 50% chord | Remove Airfoil details Airfoil plotter |
(naca001234-il) NACA 0012-34 | NACA 0012-34 airfoil Max thickness 12% at 40% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
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Polars for (hq2510-il,cp-180-050-gn,naca65209-il,naca001234-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| hq2510-il | 50,000 | 9 | 37 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq2510-il | 50,000 | 5 | 38.6 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq2510-il | 100,000 | 9 | 57.5 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq2510-il | 100,000 | 5 | 55.9 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq2510-il | 200,000 | 9 | 79.1 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq2510-il | 200,000 | 5 | 72.1 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq2510-il | 500,000 | 9 | 105.6 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq2510-il | 500,000 | 5 | 85.3 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq2510-il | 1,000,000 | 9 | 113.7 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq2510-il | 1,000,000 | 5 | 92.5 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| cp-180-050-gn | 50,000 | 9 | 16.1 at α=17° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| cp-180-050-gn | 50,000 | 5 | 13.5 at α=18.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| cp-180-050-gn | 50,000 | 1 | 10.9 at α=10° | Mach=0 Ncrit=1 | Xfoil prediction | Details | |
| cp-180-050-gn | 100,000 | 9 | 15 at α=10.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| cp-180-050-gn | 100,000 | 5 | 15 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| cp-180-050-gn | 100,000 | 1 | 16.7 at α=8.25° | Mach=0 Ncrit=1 | Xfoil prediction | Details | |
| cp-180-050-gn | 200,000 | 9 | 29.7 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| cp-180-050-gn | 200,000 | 5 | 29.6 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| cp-180-050-gn | 200,000 | 1 | 28.9 at α=5.75° | Mach=0 Ncrit=1 | Xfoil prediction | Details | |
| cp-180-050-gn | 500,000 | 9 | 55.3 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| cp-180-050-gn | 500,000 | 5 | 46.7 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| cp-180-050-gn | 500,000 | 1 | 33.5 at α=3° | Mach=0 Ncrit=1 | Xfoil prediction | Details | |
| cp-180-050-gn | 1,000,000 | 9 | 52.3 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| cp-180-050-gn | 1,000,000 | 5 | 47.5 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| cp-180-050-gn | 1,000,000 | 1 | 29.8 at α=2° | Mach=0 Ncrit=1 | Xfoil prediction | Details | |
| naca65209-il | 50,000 | 9 | 24.9 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca65209-il | 50,000 | 5 | 30.4 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca65209-il | 100,000 | 9 | 43.6 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca65209-il | 100,000 | 5 | 42.1 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca65209-il | 200,000 | 9 | 59.3 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca65209-il | 200,000 | 5 | 50.4 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca65209-il | 500,000 | 9 | 71.3 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca65209-il | 500,000 | 5 | 61.2 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca65209-il | 1,000,000 | 9 | 80.6 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca65209-il | 1,000,000 | 5 | 68 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca001234-il | 50,000 | 9 | 25.9 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca001234-il | 50,000 | 5 | 27.5 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca001234-il | 100,000 | 9 | 39.2 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca001234-il | 100,000 | 5 | 36.7 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca001234-il | 200,000 | 9 | 47.6 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca001234-il | 200,000 | 5 | 39.7 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca001234-il | 500,000 | 9 | 49.1 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca001234-il | 500,000 | 5 | 45.6 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca001234-il | 1,000,000 | 9 | 56.4 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca001234-il | 1,000,000 | 5 | 55.7 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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