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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(m26-il) NACA M26 AIRFOIL | NACA/Munk M-26 airfoil Max thickness 8.3% at 40% chord Max camber 8.3% at 30% chord | Remove Airfoil details Airfoil plotter |
(isa962-il) I.S.A. 962 | I.S.A. 962 airfoil Max thickness 9.6% at 20% chord Max camber 4.6% at 40% chord | Remove Airfoil details Airfoil plotter |
(tempest1-il) HAWKER TEMPEST 37.5% SEMISPAN AIRFOIL | Hawker Tempest 37.5% semispan airfoil (NPL?) Max thickness 14.5% at 38.3% chord Max camber 1% at 40.4% chord | Remove Airfoil details Airfoil plotter |
(th25816-il) TH 25816 HALE AIRFOIL | Naval Air Development Center/Doug Hall high altitude Max thickness 25.7% at 48.3% chord Max camber 4% at 52.9% chord | Remove Airfoil details Airfoil plotter |
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Polars for (m26-il,isa962-il,tempest1-il,th25816-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| m26-il | 50,000 | 9 | 6.1 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m26-il | 50,000 | 5 | 14 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m26-il | 100,000 | 9 | 16.6 at α=12° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m26-il | 100,000 | 5 | 41.4 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m26-il | 200,000 | 9 | 78.7 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m26-il | 200,000 | 5 | 78.3 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m26-il | 500,000 | 9 | 115.7 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m26-il | 500,000 | 5 | 98.7 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m26-il | 1,000,000 | 9 | 141.1 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m26-il | 1,000,000 | 5 | 113.7 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| isa962-il | 50,000 | 9 | 36.2 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| isa962-il | 50,000 | 5 | 39.4 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| isa962-il | 100,000 | 9 | 57.5 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| isa962-il | 100,000 | 5 | 56.1 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| isa962-il | 200,000 | 9 | 77.1 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| isa962-il | 200,000 | 5 | 69.8 at α=2° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| isa962-il | 500,000 | 9 | 98.7 at α=1.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| isa962-il | 500,000 | 5 | 88.3 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| isa962-il | 1,000,000 | 9 | 111.8 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| isa962-il | 1,000,000 | 5 | 102.5 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| tempest1-il | 50,000 | 9 | 30.9 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| tempest1-il | 50,000 | 5 | 30.2 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| tempest1-il | 100,000 | 9 | 49.8 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| tempest1-il | 100,000 | 5 | 47.7 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| tempest1-il | 200,000 | 9 | 67 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| tempest1-il | 200,000 | 5 | 53.7 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| tempest1-il | 500,000 | 9 | 71.5 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| tempest1-il | 500,000 | 5 | 62.2 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| tempest1-il | 1,000,000 | 9 | 81.5 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| tempest1-il | 1,000,000 | 5 | 68.6 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| th25816-il | 50,000 | 9 | 2.4 at α=13.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| th25816-il | 50,000 | 5 | 7.1 at α=19° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| th25816-il | 100,000 | 9 | 15.1 at α=17.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| th25816-il | 100,000 | 5 | 12.2 at α=16° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| th25816-il | 200,000 | 9 | 21.5 at α=14.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| th25816-il | 200,000 | 5 | 19.1 at α=13.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| th25816-il | 500,000 | 9 | 54.7 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| th25816-il | 500,000 | 5 | 47.9 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| th25816-il | 1,000,000 | 9 | 74.9 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| th25816-il | 1,000,000 | 5 | 59.6 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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