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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(be50-il) BE50 (original) | Verbitsky BE50 free flight airfoil (original) Max thickness 7.3% at 25% chord Max camber 4.1% at 45% chord | Remove Airfoil details Airfoil plotter |
(vr7-il) BOEING-VERTOL VR-7 AIRFOIL | Boeing-Vertol VR-7 rotorcraft airfoil Max thickness 12% at 33% chord Max camber 3.1% at 33% chord | Remove Airfoil details Airfoil plotter |
(s1221-il) S1221 w/o flap | Selig S1221 airfoil Max thickness 12.1% at 21.8% chord Max camber 4.9% at 49.1% chord | Remove Airfoil details Airfoil plotter |
(dae31-il) DAE-31 AIRFOIL | Drela DAE31 low Reynolds number airfoil Max thickness 11.1% at 29.3% chord Max camber 6.7% at 47% chord | Remove Airfoil details Airfoil plotter |
(s1223-il) S1223 | Selig S1223 high lift low Reynolds number airfoil Max thickness 12.1% at 19.8% chord Max camber 8.1% at 49% chord | Remove Airfoil details Airfoil plotter |
(tempest3-il) HAWKER TEMPEST 96.77% SEMISPAN AIRFOIL | Hawker Tempest 96.77% semispan airfoil (NPL?) Max thickness 10% at 38.7% chord Max camber 1% at 40.7% chord | Remove Airfoil details Airfoil plotter |
(c5a-il) LOCKHEED C-5A BL0 AIRFOIL | Lockheed-Georgia C-5A transonic wing airfoils Max thickness 13.1% at 40% chord Max camber 0.7% at 85% chord | Remove Airfoil details Airfoil plotter |
(be50sm-il) BE50 (smoothed) | Verbitsky BE50 free flight airfoil (original) Max thickness 7.3% at 23.8% chord Max camber 4% at 45.4% chord | Remove Airfoil details Airfoil plotter |
(s102b-il) SOMERS S102 AIRFOIL (BLUNT) | Dan Somers airfoil for the Toyota general aviation airplane Max thickness 15% at 40% chord Max camber 2% at 68.7% chord | Remove Airfoil details Airfoil plotter |
(c141f-il) LOCKHEED C-141 BL958.89 AIRFOIL | Lockheed-Georgia C-141 transonic wing airfoils Max thickness 10% at 40.2% chord Max camber 2.3% at 45.1% chord | Remove Airfoil details Airfoil plotter |
(df101-il) DF 101 AIRFOIL | David Fraser DF 101 low Reynolds number airfoil Max thickness 11% at 29.1% chord Max camber 2.3% at 43.5% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (be50-il,vr7-il,s1221-il,dae31-il,s1223-il,tempest3-il,c5a-il,be50sm-il,s102b-il,c141f-il,df101-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| be50-il | 50,000 | 9 | 38.3 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| be50-il | 50,000 | 5 | 43.1 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| be50-il | 100,000 | 9 | 59.7 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| be50-il | 100,000 | 5 | 59.7 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| be50-il | 200,000 | 9 | 79.8 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| be50-il | 200,000 | 5 | 73.9 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| be50-il | 500,000 | 9 | 102.1 at α=1.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| be50-il | 500,000 | 5 | 95.4 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| be50-il | 1,000,000 | 9 | 118.2 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| be50-il | 1,000,000 | 5 | 110.1 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| vr7-il | 50,000 | 9 | 29 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| vr7-il | 50,000 | 5 | 32.1 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| vr7-il | 100,000 | 9 | 51.7 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| vr7-il | 100,000 | 5 | 53.5 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| vr7-il | 200,000 | 9 | 73.7 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| vr7-il | 200,000 | 5 | 72.3 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| vr7-il | 500,000 | 9 | 103 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| vr7-il | 500,000 | 5 | 96.2 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| vr7-il | 1,000,000 | 9 | 125 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| vr7-il | 1,000,000 | 5 | 113.1 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1221-il | 50,000 | 9 | 27.1 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1221-il | 50,000 | 5 | 36.6 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1221-il | 100,000 | 9 | 45.2 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1221-il | 100,000 | 5 | 54.5 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1221-il | 200,000 | 9 | 70 at α=11.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1221-il | 200,000 | 5 | 76.5 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1221-il | 500,000 | 9 | 107.5 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1221-il | 500,000 | 5 | 110 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1221-il | 1,000,000 | 9 | 137.9 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1221-il | 1,000,000 | 5 | 135.1 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| dae31-il | 50,000 | 9 | 10 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| dae31-il | 50,000 | 5 | 25.9 at α=10° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| dae31-il | 100,000 | 9 | 56.4 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| dae31-il | 100,000 | 5 | 57.2 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| dae31-il | 200,000 | 9 | 91.3 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| dae31-il | 200,000 | 5 | 90.8 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| dae31-il | 500,000 | 9 | 139.4 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| dae31-il | 500,000 | 5 | 128.8 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| dae31-il | 1,000,000 | 9 | 173.7 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| dae31-il | 1,000,000 | 5 | 151.5 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1223-il | 50,000 | 9 | 33.1 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1223-il | 50,000 | 5 | 42.3 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1223-il | 100,000 | 9 | 54.5 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1223-il | 100,000 | 5 | 59.2 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1223-il | 200,000 | 9 | 73.6 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1223-il | 200,000 | 5 | 75.3 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1223-il | 500,000 | 9 | 98.8 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1223-il | 500,000 | 5 | 97.4 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1223-il | 1,000,000 | 9 | 121.4 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1223-il | 1,000,000 | 5 | 120 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| tempest3-il | 50,000 | 9 | 33.3 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| tempest3-il | 50,000 | 5 | 32.5 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| tempest3-il | 100,000 | 9 | 49.4 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| tempest3-il | 100,000 | 5 | 46.9 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| tempest3-il | 200,000 | 9 | 65.2 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| tempest3-il | 200,000 | 5 | 58.8 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| tempest3-il | 500,000 | 9 | 76.1 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| tempest3-il | 500,000 | 5 | 63.1 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| tempest3-il | 1,000,000 | 9 | 80.6 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| tempest3-il | 1,000,000 | 5 | 70.2 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| c5a-il | 50,000 | 9 | 27.2 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c5a-il | 50,000 | 5 | 27.1 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| c5a-il | 100,000 | 9 | 41.5 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c5a-il | 100,000 | 5 | 32.5 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| c5a-il | 200,000 | 9 | 44.9 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c5a-il | 200,000 | 5 | 40.7 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| c5a-il | 500,000 | 9 | 56.8 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c5a-il | 500,000 | 5 | 55.8 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| c5a-il | 1,000,000 | 9 | 68.9 at α=10.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c5a-il | 1,000,000 | 5 | 72.3 at α=9.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| be50sm-il | 50,000 | 9 | 38.9 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| be50sm-il | 50,000 | 5 | 43 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| be50sm-il | 100,000 | 9 | 60.5 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| be50sm-il | 100,000 | 5 | 59.2 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| be50sm-il | 200,000 | 9 | 81.2 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| be50sm-il | 200,000 | 5 | 74.4 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| be50sm-il | 500,000 | 9 | 104.9 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| be50sm-il | 500,000 | 5 | 97.8 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| be50sm-il | 1,000,000 | 9 | 121.5 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| be50sm-il | 1,000,000 | 5 | 115.9 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s102b-il | 50,000 | 9 | 31.1 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s102b-il | 50,000 | 5 | 28.1 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s102b-il | 100,000 | 9 | 42.6 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s102b-il | 100,000 | 5 | 43.8 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s102b-il | 200,000 | 9 | 60.5 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s102b-il | 200,000 | 5 | 57.6 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s102b-il | 500,000 | 9 | 81.9 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s102b-il | 500,000 | 5 | 70.7 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s102b-il | 1,000,000 | 9 | 96.4 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s102b-il | 1,000,000 | 5 | 85.3 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| c141f-il | 50,000 | 9 | 34.6 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c141f-il | 50,000 | 5 | 32.6 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| c141f-il | 100,000 | 9 | 50.9 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c141f-il | 100,000 | 5 | 46.1 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| c141f-il | 200,000 | 9 | 69.5 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c141f-il | 200,000 | 5 | 59.3 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| c141f-il | 500,000 | 9 | 89 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c141f-il | 500,000 | 5 | 70 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| c141f-il | 1,000,000 | 9 | 89.7 at α=1.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c141f-il | 1,000,000 | 5 | 86.3 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| df101-il | 50,000 | 9 | 31.5 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| df101-il | 50,000 | 5 | 34.8 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| df101-il | 100,000 | 9 | 50.5 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| df101-il | 100,000 | 5 | 49.6 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| df101-il | 200,000 | 9 | 68.7 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| df101-il | 200,000 | 5 | 63 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| df101-il | 500,000 | 9 | 90.9 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| df101-il | 500,000 | 5 | 80.5 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| df101-il | 1,000,000 | 9 | 104.4 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| df101-il | 1,000,000 | 5 | 96.2 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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