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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(b707d-il) BOEING 707 .54 SPAN AIRFOIL | Boeing Commercial Airplane Company model 707 airfoils Max thickness 9% at 40% chord Max camber 1.8% at 30% chord | Remove Airfoil details Airfoil plotter |
(b540ols-il) BELL 540 AIRFOIL (MODIFIED NACA 0012) | Bell AH-1 rotor blade airfoil (operational loads survey) Max thickness 9.7% at 22.1% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
(m24-il) NACA M24 AIRFOIL | NACA/Munk M-24 airfoil Max thickness 12% at 30.1% chord Max camber 6.3% at 30.1% chord | Remove Airfoil details Airfoil plotter |
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Polars for (b707d-il,b540ols-il,m24-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| b707d-il | 50,000 | 9 | 36.7 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| b707d-il | 50,000 | 5 | 35.8 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| b707d-il | 100,000 | 9 | 53.9 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| b707d-il | 100,000 | 5 | 47.8 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| b707d-il | 200,000 | 9 | 70.3 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| b707d-il | 200,000 | 5 | 52.3 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| b707d-il | 500,000 | 9 | 80.1 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| b707d-il | 500,000 | 5 | 62.3 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| b707d-il | 1,000,000 | 9 | 75.9 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| b707d-il | 1,000,000 | 5 | 76.9 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| b540ols-il | 50,000 | 9 | 21.3 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| b540ols-il | 50,000 | 5 | 24.9 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| b540ols-il | 100,000 | 9 | 31.5 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| b540ols-il | 100,000 | 5 | 34.1 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| b540ols-il | 200,000 | 9 | 42.5 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| b540ols-il | 200,000 | 5 | 44.9 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| b540ols-il | 500,000 | 9 | 59.4 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| b540ols-il | 500,000 | 5 | 62.1 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| b540ols-il | 1,000,000 | 9 | 74.8 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| b540ols-il | 1,000,000 | 5 | 76.5 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m24-il | 50,000 | 9 | 5.1 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m24-il | 50,000 | 5 | 19.9 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m24-il | 100,000 | 9 | 25.5 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m24-il | 100,000 | 5 | 45.2 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m24-il | 200,000 | 9 | 67.9 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m24-il | 200,000 | 5 | 71.2 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m24-il | 500,000 | 9 | 104.2 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m24-il | 500,000 | 5 | 100.6 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m24-il | 1,000,000 | 9 | 129.3 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m24-il | 1,000,000 | 5 | 118.9 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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