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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(b737d-il) BOEING 737 OUTBOARD AIRFOIL | Boeing Commercial Airplane Company model 737 airfoils Max thickness 10.8% at 40% chord Max camber 1.6% at 20% chord | Remove Airfoil details Airfoil plotter |
(davis-il) Davis AIRFOIL | Consolidated/Davis airfoil (B-24 wing?) Max thickness 11.3% at 30% chord Max camber 3.7% at 40% chord | Remove Airfoil details Airfoil plotter |
(r140-il) R140 (original) | R140 Quickee 500 airfoil (original) Max thickness 12% at 39.3% chord Max camber 0.5% at 42.3% chord | Remove Airfoil details Airfoil plotter |
(giiii-il) GIII BL288 AIRFOIL | Grumman/Gulfstream GIII transonic airfoils Max thickness 8.5% at 40% chord Max camber 1.3% at 25% chord | Remove Airfoil details Airfoil plotter |
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Polars for (b737d-il,davis-il,r140-il,giiii-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| b737d-il | 50,000 | 9 | 33.7 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| b737d-il | 50,000 | 5 | 34.3 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| b737d-il | 100,000 | 9 | 50.9 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| b737d-il | 100,000 | 5 | 48.8 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| b737d-il | 200,000 | 9 | 68.7 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| b737d-il | 200,000 | 5 | 62.3 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| b737d-il | 500,000 | 9 | 89.8 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| b737d-il | 500,000 | 5 | 71.9 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| b737d-il | 1,000,000 | 9 | 95.3 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| b737d-il | 1,000,000 | 5 | 80.7 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| davis-il | 50,000 | 9 | 22.2 at α=11° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| davis-il | 50,000 | 5 | 36.4 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| davis-il | 100,000 | 9 | 54 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| davis-il | 100,000 | 5 | 55 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| davis-il | 200,000 | 9 | 76.1 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| davis-il | 200,000 | 5 | 72.1 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| davis-il | 500,000 | 9 | 101.4 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| davis-il | 500,000 | 5 | 91.3 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| davis-il | 1,000,000 | 9 | 120.8 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| davis-il | 1,000,000 | 5 | 107 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| r140-il | 50,000 | 9 | 27.1 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| r140-il | 50,000 | 5 | 28.7 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| r140-il | 100,000 | 9 | 43.2 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| r140-il | 100,000 | 5 | 36.1 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| r140-il | 200,000 | 9 | 48.6 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| r140-il | 200,000 | 5 | 33.4 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| r140-il | 500,000 | 9 | 47.1 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| r140-il | 500,000 | 5 | 37.5 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| r140-il | 1,000,000 | 9 | 50.8 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| r140-il | 1,000,000 | 5 | 71.7 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| giiii-il | 50,000 | 9 | 33.5 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiii-il | 50,000 | 5 | 32.6 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| giiii-il | 100,000 | 9 | 47.5 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiii-il | 100,000 | 5 | 43.9 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| giiii-il | 200,000 | 9 | 61.1 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiii-il | 200,000 | 5 | 53.5 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| giiii-il | 500,000 | 9 | 75.3 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiii-il | 500,000 | 5 | 63.3 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| giiii-il | 1,000,000 | 9 | 79.2 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiii-il | 1,000,000 | 5 | 78 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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