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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(b707b-il) BOEING 707 .19 SPAN AIRFOIL | Boeing Commercial Airplane Company model 707 airfoils Max thickness 12.1% at 29.9% chord Max camber 0.7% at 9.9% chord | Remove Airfoil details Airfoil plotter |
(s826-nr) NREL's S826 Airfoil | NREL HAWT airfoil S826 tip 14.0% Dia=20 to 40 m Re=1.5E+6 Clmax(S)=1.42 Clmax(R)=1.31 High max lift coef Max thickness 14% at 33.7% chord Max camber 4.3% at 62% chord | Remove Airfoil details Airfoil plotter |
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Polars for (b707b-il,s826-nr)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| b707b-il | 50,000 | 9 | 24.7 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| b707b-il | 50,000 | 5 | 22.6 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| b707b-il | 100,000 | 9 | 30 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| b707b-il | 100,000 | 5 | 31.2 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| b707b-il | 200,000 | 9 | 39.1 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| b707b-il | 200,000 | 5 | 40.3 at α=9.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| b707b-il | 500,000 | 9 | 60.9 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| b707b-il | 500,000 | 5 | 54.9 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| b707b-il | 1,000,000 | 9 | 67 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| b707b-il | 1,000,000 | 5 | 62.7 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s826-nr | 50,000 | 9 | 34.6 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s826-nr | 50,000 | 5 | 34.4 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s826-nr | 100,000 | 9 | 60.9 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s826-nr | 100,000 | 5 | 60 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s826-nr | 200,000 | 9 | 83 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s826-nr | 200,000 | 5 | 81.4 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s826-nr | 500,000 | 9 | 114 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s826-nr | 500,000 | 5 | 107.7 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s826-nr | 1,000,000 | 9 | 137.7 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s826-nr | 1,000,000 | 5 | 126.7 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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