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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(ah81131-il) AH 81-131 | Althaus AH 81-131 airfoil Max thickness 13.1% at 40.2% chord Max camber 2.8% at 40.2% chord | Remove Airfoil details Airfoil plotter |
(lrn1015-il) NASA LRN 1015 (NASA TM 102840) | LRN 1015 airfoil used on the Northrop Grumman RQ-4 Global Hawk airfoil Max thickness 15.2% at 40% chord Max camber 4.9% at 44% chord | Remove Airfoil details Airfoil plotter |
(sd7037-il) SD7037-092-88 | Selig/Donovan SD7037 low Reynolds number airfoil Max thickness 9.2% at 26.1% chord Max camber 2.5% at 44.7% chord | Remove Airfoil details Airfoil plotter |
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Polars for (ah81131-il,lrn1015-il,sd7037-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| ah81131-il | 50,000 | 9 | 23.4 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah81131-il | 50,000 | 5 | 21.5 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah81131-il | 100,000 | 9 | 37.5 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah81131-il | 100,000 | 5 | 38.1 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah81131-il | 200,000 | 9 | 72.2 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah81131-il | 200,000 | 5 | 70.6 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah81131-il | 500,000 | 9 | 110 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah81131-il | 500,000 | 5 | 95.8 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah81131-il | 1,000,000 | 9 | 126.8 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah81131-il | 1,000,000 | 5 | 104.8 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| lrn1015-il | 50,000 | 9 | 21.9 at α=12.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| lrn1015-il | 50,000 | 5 | 20.2 at α=11° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| lrn1015-il | 100,000 | 9 | 39.8 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| lrn1015-il | 100,000 | 5 | 34 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| lrn1015-il | 200,000 | 9 | 70.8 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| lrn1015-il | 200,000 | 5 | 72.6 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| lrn1015-il | 500,000 | 9 | 127.7 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| lrn1015-il | 500,000 | 5 | 112.9 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| lrn1015-il | 1,000,000 | 9 | 154.8 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| lrn1015-il | 1,000,000 | 5 | 134.4 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sd7037-il | 50,000 | 9 | 34.5 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sd7037-il | 50,000 | 5 | 39.1 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sd7037-il | 100,000 | 9 | 55.2 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sd7037-il | 100,000 | 5 | 55.4 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sd7037-il | 200,000 | 9 | 74.7 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sd7037-il | 200,000 | 5 | 70.8 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sd7037-il | 500,000 | 9 | 99.3 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sd7037-il | 500,000 | 5 | 90.1 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sd7037-il | 1,000,000 | 9 | 116 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sd7037-il | 1,000,000 | 5 | 104.6 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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