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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(ah21-9-il) AH21 9% version (Andrew Hollom) | Andrew Hollom AH 21 airfoil (original 9% version) Max thickness 7% at 34.9% chord Max camber 1.8% at 54.8% chord | Remove Airfoil details Airfoil plotter |
(lg10sc-il) LOCKHEED-GEORGIA SUPERCRITICAL AIRFOIL | Lockheed-Georgia/NASA/Blackwell rotorcraft airfoil Max thickness 10% at 32% chord Max camber 1.5% at 16% chord | Remove Airfoil details Airfoil plotter |
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Polars for (ah21-9-il,lg10sc-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| ah21-9-il | 50,000 | 9 | 34.2 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah21-9-il | 50,000 | 5 | 34.5 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah21-9-il | 100,000 | 9 | 51.1 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah21-9-il | 100,000 | 5 | 49 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah21-9-il | 200,000 | 9 | 73.5 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah21-9-il | 200,000 | 5 | 65 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah21-9-il | 500,000 | 9 | 103.2 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah21-9-il | 500,000 | 5 | 78.4 at α=1.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah21-9-il | 1,000,000 | 9 | 113.5 at α=1.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah21-9-il | 1,000,000 | 5 | 79.6 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| lg10sc-il | 50,000 | 9 | 25.9 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| lg10sc-il | 50,000 | 5 | 27.8 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| lg10sc-il | 100,000 | 9 | 35.1 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| lg10sc-il | 100,000 | 5 | 39.1 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| lg10sc-il | 200,000 | 9 | 48.2 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| lg10sc-il | 200,000 | 5 | 53.3 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| lg10sc-il | 500,000 | 9 | 73.5 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| lg10sc-il | 500,000 | 5 | 74.6 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| lg10sc-il | 1,000,000 | 9 | 92.8 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| lg10sc-il | 1,000,000 | 5 | 90.8 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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