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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(rc10b3-il) NASA/LANGLEY RC-10(B)3 AIRFOIL | NASA/Langley RC-10(B)3 rotorcraft airfoil Max thickness 10% at 37.7% chord Max camber 1.7% at 30.3% 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 |
(sc20010-il) NASA SC(2)-0010 AIRFOIL | NASA SC(2)-0010 airfoil (NASA TP-2969) Max thickness 10% at 37% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
(rc1064c-il) NASA/LANGLEY RC10-64C AIRFOIL | NASA/Langley 10-64C rotorcraft airfoil Max thickness 10% at 40% chord Max camber 1% at 35% chord | Remove Airfoil details Airfoil plotter |
(s802-nr) NREL's S802 Airfoil | NREL HAWT airfoil S802 tip Not recommended Max thickness 11.5% at 37.9% chord Max camber 3.8% at 47.3% chord | Remove Airfoil details Airfoil plotter |
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Polars for (rc10b3-il,s9026-il,sc20010-il,rc1064c-il,s802-nr)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| rc10b3-il | 50,000 | 9 | 33.8 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rc10b3-il | 50,000 | 5 | 33.4 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rc10b3-il | 100,000 | 9 | 49.3 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rc10b3-il | 100,000 | 5 | 46.1 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rc10b3-il | 200,000 | 9 | 62.9 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rc10b3-il | 200,000 | 5 | 55.7 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rc10b3-il | 500,000 | 9 | 74.7 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rc10b3-il | 500,000 | 5 | 65.7 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rc10b3-il | 1,000,000 | 9 | 79.3 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rc10b3-il | 1,000,000 | 5 | 76.5 at α=8.75° | 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 | |
| sc20010-il | 50,000 | 9 | 23.7 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20010-il | 50,000 | 5 | 22.9 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20010-il | 100,000 | 9 | 33.1 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20010-il | 100,000 | 5 | 28.7 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20010-il | 200,000 | 9 | 39.5 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20010-il | 200,000 | 5 | 39 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20010-il | 500,000 | 9 | 52 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20010-il | 500,000 | 5 | 56.6 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20010-il | 1,000,000 | 9 | 67.7 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20010-il | 1,000,000 | 5 | 70.1 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rc1064c-il | 50,000 | 9 | 31.7 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rc1064c-il | 50,000 | 5 | 30.6 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rc1064c-il | 100,000 | 9 | 45.4 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rc1064c-il | 100,000 | 5 | 41.9 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rc1064c-il | 200,000 | 9 | 57.7 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rc1064c-il | 200,000 | 5 | 46.6 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rc1064c-il | 500,000 | 9 | 62.4 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rc1064c-il | 500,000 | 5 | 59.4 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rc1064c-il | 1,000,000 | 9 | 71.2 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rc1064c-il | 1,000,000 | 5 | 73.2 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s802-nr | 50,000 | 9 | 36.7 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s802-nr | 50,000 | 5 | 33.8 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s802-nr | 100,000 | 9 | 61 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s802-nr | 100,000 | 5 | 60.2 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s802-nr | 200,000 | 9 | 91.3 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s802-nr | 200,000 | 5 | 85.7 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s802-nr | 500,000 | 9 | 124.3 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s802-nr | 500,000 | 5 | 113.6 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s802-nr | 1,000,000 | 9 | 149.5 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s802-nr | 1,000,000 | 5 | 132.5 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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