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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(e851-il) EPPLER E851 AIRFOIL | Eppler E851 propeller airfoil Max thickness 9% at 37% chord Max camber 2.3% at 66.3% chord | Remove Airfoil details Airfoil plotter |
(e852-il) EPPLER E852 AIRFOIL | Eppler E852 propeller airfoil Max thickness 10.1% at 37.2% chord Max camber 2.8% at 61.2% chord | Remove Airfoil details Airfoil plotter |
(rg12-il) RG-12 | Rolf Girsberger RG 12 airfoil Max thickness 9.3% at 34.4% chord Max camber 1.4% at 34.4% chord | Remove Airfoil details Airfoil plotter |
(raf32-il) RAF 32 AIRFOIL | RAF-32 airfoil Max thickness 12.7% at 30% chord Max camber 5% at 50% chord | Remove Airfoil details Airfoil plotter |
(hq3518-il) HQ 3.5/18 AIRFOIL | Quabeck HQ 3.5/18 R/C sailplane airfoil Max thickness 18% at 35% chord Max camber 3.5% at 50% chord | Remove Airfoil details Airfoil plotter |
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Polars for (e851-il,e852-il,rg12-il,raf32-il,hq3518-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e851-il | 50,000 | 9 | 27.3 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e851-il | 50,000 | 5 | 31 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e851-il | 100,000 | 9 | 49 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e851-il | 100,000 | 5 | 50.7 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e851-il | 200,000 | 9 | 77.5 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e851-il | 200,000 | 5 | 73.5 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e851-il | 500,000 | 9 | 110.8 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e851-il | 500,000 | 5 | 90.5 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e851-il | 1,000,000 | 9 | 122.7 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e851-il | 1,000,000 | 5 | 95.7 at α=1.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e852-il | 50,000 | 9 | 36.5 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e852-il | 50,000 | 5 | 35.6 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e852-il | 100,000 | 9 | 58.6 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e852-il | 100,000 | 5 | 57.3 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e852-il | 200,000 | 9 | 84.2 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e852-il | 200,000 | 5 | 79.7 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e852-il | 500,000 | 9 | 119.6 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e852-il | 500,000 | 5 | 98.9 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e852-il | 1,000,000 | 9 | 132.1 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e852-il | 1,000,000 | 5 | 106.5 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rg12-il | 50,000 | 9 | 32.9 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rg12-il | 50,000 | 5 | 34.4 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rg12-il | 100,000 | 9 | 48.9 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rg12-il | 100,000 | 5 | 47.3 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rg12-il | 200,000 | 9 | 64.2 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rg12-il | 200,000 | 5 | 58.9 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rg12-il | 500,000 | 9 | 82.6 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rg12-il | 500,000 | 5 | 72.2 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rg12-il | 1,000,000 | 9 | 91.4 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rg12-il | 1,000,000 | 5 | 81.2 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf32-il | 50,000 | 9 | 29.2 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf32-il | 50,000 | 5 | 25.6 at α=10° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf32-il | 100,000 | 9 | 56.2 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf32-il | 100,000 | 5 | 56.3 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf32-il | 200,000 | 9 | 85.7 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf32-il | 200,000 | 5 | 84.8 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf32-il | 500,000 | 9 | 123.7 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf32-il | 500,000 | 5 | 116.6 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf32-il | 1,000,000 | 9 | 152.3 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf32-il | 1,000,000 | 5 | 134.8 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq3518-il | 50,000 | 9 | 6.9 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq3518-il | 50,000 | 5 | 21.4 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq3518-il | 100,000 | 9 | 47.8 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq3518-il | 100,000 | 5 | 43.4 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq3518-il | 200,000 | 9 | 68.1 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq3518-il | 200,000 | 5 | 61.8 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq3518-il | 500,000 | 9 | 90.6 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq3518-il | 500,000 | 5 | 78.7 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq3518-il | 1,000,000 | 9 | 105.4 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq3518-il | 1,000,000 | 5 | 89.7 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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