Airfoil database search (Symmetrical)
Search the 1638 airfoils available in the databases filtering by name, thickness and camber.
Click on an airfoil image to display a larger preview picture.
There are links to the original airfoil source and dat file and the details page with polar diagrams for a range of Reynolds numbers.
(naca64a010-il) NACA 64A-010 10.0% | Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
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| NACA 64A010 airfoil Max thickness 10% at 40% chord Max camber 0% at 0% chord Max Cl/Cd 26.2 at Re# 50,000 Source UIUC Airfoil Coordinates Database
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(rae104-il) RAE 104 AIRFOIL | Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
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| RAE 104 airfoil Max thickness 10% at 42% chord Max camber 0% at 0% chord Max Cl/Cd 26.2 at Re# 50,000 Source UIUC Airfoil Coordinates Database
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(lwk80100-il) LWK 80-100 | Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
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| LWK 80-100 symmetrical airfoil Max thickness 10.1% at 40.2% chord Max camber 0% at 0% chord Max Cl/Cd 26.2 at Re# 50,000 Source UIUC Airfoil Coordinates Database
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(sd8020-il) SD8020-010-88 | Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
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| Selig/Donovan SD8020 low Reynolds number airfoil Max thickness 10.1% at 27.5% chord Max camber 0% at 42.1% chord Max Cl/Cd 26.1 at Re# 50,000 Source UIUC Airfoil Coordinates Database
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(fx76100-il) WORTMANN FX 76-100 | Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
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| Wortmann FX 76-100 symmetrical airfoil Max thickness 10.1% at 27.9% chord Max camber 0% at 0% chord Max Cl/Cd 26.1 at Re# 50,000 Source UIUC Airfoil Coordinates Database
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(rae100-il) RAE 100 AIRFOIL | Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
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| RAE 100 airfoil Max thickness 10% at 26% chord Max camber 0% at 0% chord Max Cl/Cd 26.1 at Re# 50,000 Source UIUC Airfoil Coordinates Database
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(naca0010-il) NACA 0010 | Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
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| NACA 0010 airfoil Max thickness 10% at 30% chord Max camber 0% at 0% chord Max Cl/Cd 25.9 at Re# 50,000 Source UIUC Airfoil Coordinates Database
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(lwk79100-il) LWK 79-100 | Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
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| LWK 79-100 symmetrical airfoil Max thickness 10% at 27.9% chord Max camber 0% at 0% chord Max Cl/Cd 25.9 at Re# 50,000 Source UIUC Airfoil Coordinates Database
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(naca001064-il) NACA 0010-64 | Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
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| NACA 0010-64 airfoil Max thickness 10% at 40% chord Max camber 0% at 0% chord Max Cl/Cd 25.8 at Re# 50,000 Source UIUC Airfoil Coordinates Database
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(naca0010-il) NACA 0010 | Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
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| NACA 0010 airfoil Max thickness 10% at 30% chord Max camber 0% at 0% chord Max Cl/Cd 25.7 at Re# 50,000 Source UIUC Airfoil Coordinates Database
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