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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(prandtl-d-tip-ns) Prandtl-D tip - NASA Preliminary Research Aerodynamic Design To Lower Drag | NASA Preliminary Research Aerodynamic Design To Lower Drag (PRANDTL-D) glider tip airfoil Max thickness 9.6% at 26.8% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
(glennmartin4-il) Glenn Martin 4 | Glenn Martin 4 airfoil Max thickness 15.5% at 30% chord Max camber 6% at 30% chord | Remove Airfoil details Airfoil plotter |
(glennmartin2-il) Glenn Martin 2 | Glenn Martin 2 airfoil Max thickness 13.5% at 20% chord Max camber 6.1% at 30% chord | Remove Airfoil details Airfoil plotter |
(glennmartin3-il) Glenn Martin 3 | Glenn Martin 3 airfoil Max thickness 13.8% at 30% chord Max camber 4.6% at 30% chord | Remove Airfoil details Airfoil plotter |
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Polars for (prandtl-d-tip-ns,glennmartin4-il,glennmartin2-il,glennmartin3-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| prandtl-d-tip-ns | 50,000 | 9 | 25.4 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| prandtl-d-tip-ns | 100,000 | 9 | 35.8 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| prandtl-d-tip-ns | 200,000 | 9 | 47.1 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| prandtl-d-tip-ns | 500,000 | 9 | 62.7 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| prandtl-d-tip-ns | 1,000,000 | 9 | 74.6 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| prandtl-d-tip-ns | 2,000,000 | 9 | 87.3 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| prandtl-d-tip-ns | 5,000,000 | 9 | 102.8 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| glennmartin4-il | 50,000 | 9 | 22 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| glennmartin4-il | 50,000 | 5 | 27.8 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| glennmartin4-il | 100,000 | 9 | 42.8 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| glennmartin4-il | 100,000 | 5 | 40.9 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| glennmartin4-il | 200,000 | 9 | 54.7 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| glennmartin4-il | 200,000 | 5 | 49.7 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| glennmartin4-il | 500,000 | 9 | 64.9 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| glennmartin4-il | 500,000 | 5 | 62.8 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| glennmartin4-il | 1,000,000 | 9 | 79.4 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| glennmartin4-il | 1,000,000 | 5 | 77.5 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| glennmartin2-il | 50,000 | 9 | 24.7 at α=1.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| glennmartin2-il | 50,000 | 5 | 31.7 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| glennmartin2-il | 100,000 | 9 | 46.2 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| glennmartin2-il | 100,000 | 5 | 45.8 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| glennmartin2-il | 200,000 | 9 | 58.7 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| glennmartin2-il | 200,000 | 5 | 57.9 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| glennmartin2-il | 500,000 | 9 | 78.4 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| glennmartin2-il | 500,000 | 5 | 78.6 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| glennmartin2-il | 1,000,000 | 9 | 102.4 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| glennmartin2-il | 1,000,000 | 5 | 101.3 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| glennmartin3-il | 50,000 | 9 | 32.5 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| glennmartin3-il | 50,000 | 5 | 29.1 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| glennmartin3-il | 100,000 | 9 | 41.6 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| glennmartin3-il | 100,000 | 5 | 38.4 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| glennmartin3-il | 200,000 | 9 | 54.8 at α=1° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| glennmartin3-il | 200,000 | 5 | 47.1 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| glennmartin3-il | 500,000 | 9 | 62.8 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| glennmartin3-il | 500,000 | 5 | 62.6 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| glennmartin3-il | 1,000,000 | 9 | 78.7 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| glennmartin3-il | 1,000,000 | 5 | 78.2 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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