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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(s815-nr) NREL's S815 Airfoil | NREL HAWT airfoil S815 root 26.0% Dia=20 to 30 m Re=1.2E+6 Clmax(S)=1.46 Clmax(R)=1.40 High max lift coef Max thickness 26.2% at 25.7% chord Max camber 2.9% at 77.9% chord | Remove Airfoil details Airfoil plotter |
(naca642215-il) NACA 64(2)-215 | NACA 64(2)-215 airfoil Max thickness 15% at 34.9% chord Max camber 1.1% at 50% chord | Remove Airfoil details Airfoil plotter |
(ah85l120-il) AH 85-L-120/17 | Althaus AH 85-L-120/17 symmetrical airfoil Max thickness 12.1% at 43.5% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
(naca001064-il) NACA 0010-64 | NACA 0010-64 airfoil Max thickness 10% at 40% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
(hq1585-il) HQ 1.5/8.5 AIRFOIL | Quabeck HQ 1.5/8.5 R/C sailplane airfoil Max thickness 8.6% at 35% chord Max camber 1.5% at 50% chord | Remove Airfoil details Airfoil plotter |
(hq2090sm-il) HQ-2.0/9 9.0% smoothed | Quabeck HQ 2.0/9 R/C sailplane airfoil (smoothed) Max thickness 9% at 35% chord Max camber 2% at 50% chord | Remove Airfoil details Airfoil plotter |
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Polars for (s815-nr,naca642215-il,ah85l120-il,naca001064-il,hq1585-il,hq2090sm-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| s815-nr | 50,000 | 9 | 3.2 at α=-1.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s815-nr | 50,000 | 5 | 9 at α=15.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s815-nr | 100,000 | 9 | 26.2 at α=12.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s815-nr | 100,000 | 5 | 36 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s815-nr | 200,000 | 9 | 54.4 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s815-nr | 200,000 | 5 | 54.8 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s815-nr | 500,000 | 9 | 79.5 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s815-nr | 500,000 | 5 | 75.9 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s815-nr | 1,000,000 | 9 | 99.4 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s815-nr | 1,000,000 | 5 | 91.1 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca642215-il | 50,000 | 9 | 28.3 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca642215-il | 50,000 | 5 | 26.6 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca642215-il | 100,000 | 9 | 47.6 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca642215-il | 100,000 | 5 | 44.3 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca642215-il | 200,000 | 9 | 63.1 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca642215-il | 200,000 | 5 | 58.9 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca642215-il | 500,000 | 9 | 85.5 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca642215-il | 500,000 | 5 | 73.7 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca642215-il | 1,000,000 | 9 | 99.2 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca642215-il | 1,000,000 | 5 | 79.3 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah85l120-il | 50,000 | 9 | 21.4 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah85l120-il | 50,000 | 5 | 27.1 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah85l120-il | 100,000 | 9 | 37.6 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah85l120-il | 100,000 | 5 | 29.8 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah85l120-il | 200,000 | 5 | 35 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah85l120-il | 500,000 | 9 | 48.3 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah85l120-il | 500,000 | 5 | 43.5 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah85l120-il | 1,000,000 | 9 | 55.4 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah85l120-il | 1,000,000 | 5 | 52 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca001064-il | 50,000 | 9 | 25.8 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca001064-il | 50,000 | 5 | 25.2 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca001064-il | 100,000 | 9 | 36.2 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca001064-il | 100,000 | 5 | 31.7 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca001064-il | 200,000 | 9 | 43.3 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca001064-il | 200,000 | 5 | 38.7 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca001064-il | 500,000 | 9 | 49.2 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca001064-il | 500,000 | 5 | 53.7 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca001064-il | 1,000,000 | 9 | 62.5 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca001064-il | 1,000,000 | 5 | 71.6 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq1585-il | 50,000 | 9 | 35.6 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq1585-il | 50,000 | 5 | 35.6 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq1585-il | 100,000 | 9 | 51.4 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq1585-il | 100,000 | 5 | 48.4 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq1585-il | 200,000 | 9 | 67.2 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq1585-il | 200,000 | 5 | 58.3 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq1585-il | 500,000 | 9 | 84.7 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq1585-il | 500,000 | 5 | 67.3 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq1585-il | 1,000,000 | 9 | 85.3 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq1585-il | 1,000,000 | 5 | 80.4 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq2090sm-il | 50,000 | 9 | 36.9 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq2090sm-il | 50,000 | 5 | 37.9 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq2090sm-il | 100,000 | 9 | 55.1 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq2090sm-il | 100,000 | 5 | 53.5 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq2090sm-il | 200,000 | 9 | 73.9 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq2090sm-il | 200,000 | 5 | 68.3 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq2090sm-il | 500,000 | 9 | 97.2 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq2090sm-il | 500,000 | 5 | 79.3 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq2090sm-il | 1,000,000 | 9 | 104.7 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq2090sm-il | 1,000,000 | 5 | 87.2 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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