Airfoil Comparison
Select airfoils from the airfoil database or add your own airfoils and compare the airfoil shape and lift/drag polars.
| Open full size plan in new window | Open paginated plan in new window | |
| Download PDF file | SVG image as text file | |
| Clear all | ||
(sc1095r8-il) SIKORSKY SC1094R8 AIRFOIL | Sikorsky/Velkoff SC1095 R8 rotorcraft airfoil Max thickness 9.3% at 26.5% chord Max camber 2.1% at 20.5% chord | Remove Airfoil details Airfoil plotter |
(naca1412-il) NACA 1412 | NACA 1412 airfoil Max thickness 12% at 29.9% chord Max camber 1% at 40% chord | Remove Airfoil details Airfoil plotter |
(rc12n1-il) NASA/LANGLEY RC-12(N)1 AIRFOIL | NASA/Langley RC-12(N)1 rotorcraft airfoil Max thickness 12% at 37.4% chord Max camber 1.4% at 30% chord | Remove Airfoil details Airfoil plotter |
(nl722362-il) NLR-7223-62 AIRFOIL | NLR NLR-7223-62 transonic rotorcraft airfoil Max thickness 8.6% at 38% chord Max camber 1.3% at 21.6% chord | Remove Airfoil details Airfoil plotter |
(ste87391-il) EPPLER STE 87(-3)-914 AIRFOIL | Eppler STE 87(-3)-914 airfoil Max thickness 14.6% at 34.1% chord Max camber 4.2% at 58.3% chord | Remove Airfoil details Airfoil plotter |
(s805a-nr) NREL's S805A Airfoil | NREL HAWT airfoil S805A primary Max thickness 13.5% at 40% chord Max camber 2.1% at 35% chord | Remove Airfoil details Airfoil plotter |
(s9026-il) S9026 (9.5%) | Selig S9026 (9.5%) symmetrical horizontal stab airfoil used on the Opus R/C sailplane Max thickness 9.5% at 27.3% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
(s814-nr) NREL's S814 Airfoil | NREL HAWT airfoil S814 root 24.0% Dia=20 to 30 m Re=1.5E+6 Clmax(S)=1.56 Clmax(R)=1.51 High max lift coef Max thickness 24.1% at 28.4% chord Max camber 3% at 74.5% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (sc1095r8-il,naca1412-il,rc12n1-il,nl722362-il,ste87391-il,s805a-nr,s9026-il,s814-nr)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| sc1095r8-il | 50,000 | 9 | 24.4 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc1095r8-il | 50,000 | 5 | 27 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc1095r8-il | 100,000 | 9 | 33.6 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc1095r8-il | 100,000 | 5 | 37.6 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc1095r8-il | 200,000 | 9 | 45.3 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc1095r8-il | 200,000 | 5 | 50.6 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc1095r8-il | 500,000 | 9 | 67.8 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc1095r8-il | 500,000 | 5 | 72.6 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc1095r8-il | 1,000,000 | 9 | 88 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc1095r8-il | 1,000,000 | 5 | 91.7 at α=10.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca1412-il | 50,000 | 9 | 29.6 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca1412-il | 50,000 | 5 | 31.2 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca1412-il | 100,000 | 9 | 44.1 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca1412-il | 100,000 | 5 | 43 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca1412-il | 200,000 | 9 | 57.6 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca1412-il | 200,000 | 5 | 53.3 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca1412-il | 500,000 | 9 | 73.5 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca1412-il | 500,000 | 5 | 66 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca1412-il | 1,000,000 | 9 | 83.8 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca1412-il | 1,000,000 | 5 | 78.6 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rc12n1-il | 50,000 | 9 | 32 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rc12n1-il | 50,000 | 5 | 31.9 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rc12n1-il | 100,000 | 9 | 49.2 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rc12n1-il | 100,000 | 5 | 47.2 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rc12n1-il | 200,000 | 9 | 66.6 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rc12n1-il | 200,000 | 5 | 61 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rc12n1-il | 500,000 | 9 | 86.5 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rc12n1-il | 500,000 | 5 | 70.4 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rc12n1-il | 1,000,000 | 9 | 92.9 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rc12n1-il | 1,000,000 | 5 | 76.5 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nl722362-il | 50,000 | 9 | 30 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nl722362-il | 50,000 | 5 | 28.5 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nl722362-il | 100,000 | 9 | 42.2 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nl722362-il | 100,000 | 5 | 39.8 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nl722362-il | 200,000 | 9 | 57.1 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nl722362-il | 200,000 | 5 | 52.9 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nl722362-il | 500,000 | 9 | 72.8 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nl722362-il | 500,000 | 5 | 70.8 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nl722362-il | 1,000,000 | 9 | 87.9 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nl722362-il | 1,000,000 | 5 | 78.9 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ste87391-il | 50,000 | 9 | 32.2 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ste87391-il | 50,000 | 5 | 30.9 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ste87391-il | 100,000 | 9 | 51.3 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ste87391-il | 100,000 | 5 | 45.5 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ste87391-il | 200,000 | 9 | 69.5 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ste87391-il | 200,000 | 5 | 61.2 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ste87391-il | 500,000 | 9 | 97.4 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ste87391-il | 500,000 | 5 | 92.5 at α=1.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ste87391-il | 1,000,000 | 9 | 146 at α=1.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ste87391-il | 1,000,000 | 5 | 106.6 at α=-0.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s805a-nr | 50,000 | 9 | 30.1 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s805a-nr | 50,000 | 5 | 27.1 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s805a-nr | 100,000 | 9 | 50.9 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s805a-nr | 100,000 | 5 | 50.6 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s805a-nr | 200,000 | 9 | 75.6 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s805a-nr | 200,000 | 5 | 67 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s805a-nr | 500,000 | 9 | 96.9 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s805a-nr | 500,000 | 5 | 89.9 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s805a-nr | 1,000,000 | 9 | 117.4 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s805a-nr | 1,000,000 | 5 | 103.3 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s9026-il | 50,000 | 9 | 24.2 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s9026-il | 50,000 | 5 | 25.4 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s9026-il | 100,000 | 9 | 33.8 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s9026-il | 100,000 | 5 | 34.6 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s9026-il | 200,000 | 9 | 44.3 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s9026-il | 200,000 | 5 | 45.3 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s9026-il | 500,000 | 9 | 60.9 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s9026-il | 500,000 | 5 | 61.5 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s9026-il | 1,000,000 | 9 | 75.1 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s9026-il | 1,000,000 | 5 | 74.6 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s814-nr | 50,000 | 9 | 4.4 at α=14.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s814-nr | 50,000 | 5 | 10.9 at α=14° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s814-nr | 100,000 | 9 | 35.2 at α=11° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s814-nr | 100,000 | 5 | 40.1 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s814-nr | 200,000 | 9 | 58.3 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s814-nr | 200,000 | 5 | 58.8 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s814-nr | 500,000 | 9 | 84.4 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s814-nr | 500,000 | 5 | 80.8 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s814-nr | 1,000,000 | 9 | 104.7 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s814-nr | 1,000,000 | 5 | 97.1 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||