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.
(sc20010-il) NASA SC(2)-0010 AIRFOIL | Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file | |
NASA SC(2)-0010 airfoil (NASA TP-2969) Max thickness 10% at 37% chord Max camber 0% at 0% chord Max Cl/Cd 22.9 at Re# 50,000 Source UIUC Airfoil Coordinates Database | ||
(naca001066-il) NACA 0010-66 | Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file | |
NACA 0010-66 airfoil Max thickness 10% at 60% chord Max camber 0% at 0% chord Max Cl/Cd 21.9 at Re# 50,000 Source UIUC Airfoil Coordinates Database | ||
(naca001065-il) NACA 0010-65 | Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file | |
NACA 0010-65 airfoil Max thickness 10% at 50% chord Max camber 0% at 0% chord Max Cl/Cd 21.8 at Re# 50,000 Source UIUC Airfoil Coordinates Database | ||
(b540ols-il) BELL 540 AIRFOIL (MODIFIED NACA 0012) | Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file | |
Bell AH-1 rotor blade airfoil (operational loads survey) Max thickness 9.7% at 22.1% chord Max camber 0% at 0% chord Max Cl/Cd 21.3 at Re# 50,000 Source UIUC Airfoil Coordinates Database | ||
(naca001066-il) NACA 0010-66 | Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file | |
NACA 0010-66 airfoil Max thickness 10% at 60% chord Max camber 0% at 0% chord Max Cl/Cd 20.9 at Re# 50,000 Source UIUC Airfoil Coordinates Database | ||
(naca001034-il) NACA 0010-34 | Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file | |
NACA 0010-34 airfoil Max thickness 10% at 40% chord Max camber 0% at 0% chord Max Cl/Cd 20.8 at Re# 50,000 Source UIUC Airfoil Coordinates Database | ||
(naca001065-il) NACA 0010-65 | Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file | |
NACA 0010-65 airfoil Max thickness 10% at 50% chord Max camber 0% at 0% chord Max Cl/Cd 20.4 at Re# 50,000 Source UIUC Airfoil Coordinates Database | ||
(naca001035-il) NACA 0010-35 | Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file | |
NACA 0010-35 airfoil Max thickness 10% at 50% chord Max camber 0% at 0% chord Max Cl/Cd 18.8 at Re# 50,000 Source UIUC Airfoil Coordinates Database | ||
(naca001035-il) NACA 0010-35 | Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file | |
NACA 0010-35 airfoil Max thickness 10% at 50% chord Max camber 0% at 0% chord Max Cl/Cd 17.6 at Re# 50,000 Source UIUC Airfoil Coordinates Database |
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