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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(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 |
(c141d-il) LOCKHEED C-141 BL610.61 AIRFOIL | Lockheed-Georgia C-141 transonic wing airfoils Max thickness 10.8% at 40.2% chord Max camber 1.5% at 50% chord | Remove Airfoil details Airfoil plotter |
(c141e-il) LOCKHEED C-141 BL761.11 AIRFOIL | Lockheed-Georgia C-141 transonic wing airfoils Max thickness 10.5% at 40.2% chord Max camber 1.8% at 50% chord | Remove Airfoil details Airfoil plotter |
(davis-corrected-il) DAVIS BASIC B-24 WING AIRFOIL | Davis basic B-24 wing airfoil Max thickness 15.9% at 29.6% chord Max camber 2.5% at 29.6% chord | Remove Airfoil details Airfoil plotter |
(chen-il) CHEN AIRFOIL | University of Illinois at Urbana-Champaign / Chen high lift airfoil Max thickness 12.5% at 27.7% chord Max camber 7.8% at 25.4% chord | Remove Airfoil details Airfoil plotter |
(b29tip-il) B-29 TIP AIRFOIL | Boeing B-29 tip airfoil Max thickness 9% at 30% chord Max camber 2.2% at 30% chord | Remove Airfoil details Airfoil plotter |
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Polars for (davis-il,c141d-il,c141e-il,davis-corrected-il,chen-il,b29tip-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| 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 | |
| c141d-il | 50,000 | 9 | 31.5 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c141d-il | 50,000 | 5 | 30.9 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| c141d-il | 100,000 | 9 | 47.2 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c141d-il | 100,000 | 5 | 44.5 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| c141d-il | 200,000 | 9 | 67 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c141d-il | 200,000 | 5 | 57.5 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| c141d-il | 500,000 | 9 | 82.4 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c141d-il | 500,000 | 5 | 65.1 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| c141d-il | 1,000,000 | 9 | 83.6 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c141d-il | 1,000,000 | 5 | 79.3 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| c141e-il | 50,000 | 9 | 33.4 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c141e-il | 50,000 | 5 | 31.8 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| c141e-il | 100,000 | 9 | 49.2 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c141e-il | 100,000 | 5 | 45.7 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| c141e-il | 200,000 | 9 | 69.1 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c141e-il | 200,000 | 5 | 59.6 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| c141e-il | 500,000 | 9 | 88.4 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c141e-il | 500,000 | 5 | 65.2 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| c141e-il | 1,000,000 | 9 | 88.8 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c141e-il | 1,000,000 | 5 | 78.6 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| davis-corrected-il | 50,000 | 9 | 12.5 at α=-0.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| davis-corrected-il | 100,000 | 9 | 36.4 at α=11.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| davis-corrected-il | 200,000 | 9 | 63.9 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| davis-corrected-il | 500,000 | 9 | 96.3 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| davis-corrected-il | 1,000,000 | 9 | 122.3 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| davis-corrected-il | 2,000,000 | 9 | 137.5 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| davis-corrected-il | 5,000,000 | 9 | 157.6 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| chen-il | 50,000 | 9 | 4.2 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| chen-il | 50,000 | 5 | 4.8 at α=11.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| chen-il | 100,000 | 9 | 4.9 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| chen-il | 100,000 | 5 | 8.7 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| chen-il | 200,000 | 9 | 5.6 at α=11.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| chen-il | 200,000 | 5 | 19.6 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| chen-il | 500,000 | 9 | 13.6 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| chen-il | 500,000 | 5 | 56.5 at α=12° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| chen-il | 1,000,000 | 9 | 125.4 at α=14.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| chen-il | 1,000,000 | 5 | 123 at α=13° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| b29tip-il | 50,000 | 9 | 34.1 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| b29tip-il | 50,000 | 5 | 34.8 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| b29tip-il | 100,000 | 9 | 51.1 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| b29tip-il | 100,000 | 5 | 50.9 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| b29tip-il | 200,000 | 9 | 68.8 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| b29tip-il | 200,000 | 5 | 66.4 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| b29tip-il | 500,000 | 9 | 91.4 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| b29tip-il | 500,000 | 5 | 84.3 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| b29tip-il | 1,000,000 | 9 | 106.1 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| b29tip-il | 1,000,000 | 5 | 90 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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