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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(atr72sm-il) Smoothed ATR airfoil coordinates obtained using AFSMO (Harry Morgan's NASA smoothing program) | ATR 72 wing airfoil (from NTSB report) Max thickness 14.5% at 25.4% chord Max camber 2.9% at 21.4% chord | Remove Airfoil details Airfoil plotter |
(rg1495-il) RG 14 9.5% AIRFOIL | Rolf Girsberger RG 14 (9.5%) airfoil Max thickness 9.5% at 31% chord Max camber 1.6% at 36% chord | Remove Airfoil details Airfoil plotter |
(rg15a111-il) RG 15A-1.8/11.0 AIRFOIL | Rolf Girsberger RG 15A-1.8/11.0 airfoil Max thickness 11% at 30.2% chord Max camber 1.8% at 39.7% chord | Remove Airfoil details Airfoil plotter |
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Polars for (atr72sm-il,rg1495-il,rg15a111-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| atr72sm-il | 50,000 | 9 | 20.5 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| atr72sm-il | 50,000 | 5 | 25.8 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| atr72sm-il | 100,000 | 9 | 33.3 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| atr72sm-il | 100,000 | 5 | 39.1 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| atr72sm-il | 200,000 | 9 | 48.9 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| atr72sm-il | 200,000 | 5 | 55.4 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| atr72sm-il | 500,000 | 9 | 77.7 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| atr72sm-il | 500,000 | 5 | 81.6 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| atr72sm-il | 1,000,000 | 9 | 104.4 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| atr72sm-il | 1,000,000 | 5 | 105.2 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rg1495-il | 50,000 | 9 | 32.7 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rg1495-il | 50,000 | 5 | 33.9 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rg1495-il | 100,000 | 9 | 48.5 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rg1495-il | 100,000 | 5 | 46.5 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rg1495-il | 200,000 | 9 | 63.6 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rg1495-il | 200,000 | 5 | 57.9 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rg1495-il | 500,000 | 9 | 82.1 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rg1495-il | 500,000 | 5 | 71.4 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rg1495-il | 1,000,000 | 9 | 89.5 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rg1495-il | 1,000,000 | 5 | 85 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rg15a111-il | 50,000 | 9 | 32.3 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rg15a111-il | 50,000 | 5 | 35.1 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rg15a111-il | 100,000 | 9 | 50 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rg15a111-il | 100,000 | 5 | 49.5 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rg15a111-il | 200,000 | 9 | 66.8 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rg15a111-il | 200,000 | 5 | 62.7 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rg15a111-il | 500,000 | 9 | 87.9 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rg15a111-il | 500,000 | 5 | 79.7 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rg15a111-il | 1,000,000 | 9 | 101.9 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rg15a111-il | 1,000,000 | 5 | 90 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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