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.
(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 | |
Wortmann FX 76-100 symmetrical airfoil Max thickness 10.1% at 27.9% chord Max camber 0% at 0% chord Max Cl/Cd 25.6 at Re# 50,000 Source UIUC Airfoil Coordinates Database | ||
(prandtl-d-tip-ns) Prandtl-D tip - NASA Preliminary Research Aerodynamic Design To Lower Drag | Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file | |
NASA Preliminary Research Aerodynamic Design To Lower Drag (PRANDTL-D) glider tip airfoil Max thickness 9.6% at 26.8% chord Max camber 0% at 0% chord Max Cl/Cd 25.4 at Re# 50,000 Source NASA | ||
(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 | |
NACA 0010-64 airfoil Max thickness 10% at 40% chord Max camber 0% at 0% chord Max Cl/Cd 25.2 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 25.1 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 24.9 at Re# 50,000 Source UIUC Airfoil Coordinates Database | ||
(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 | |
RAE 100 airfoil Max thickness 10% at 26% chord Max camber 0% at 0% chord Max Cl/Cd 24.6 at Re# 50,000 Source UIUC Airfoil Coordinates Database | ||
(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 | |
RAE 104 airfoil Max thickness 10% at 42% chord Max camber 0% at 0% chord Max Cl/Cd 24.6 at Re# 50,000 Source UIUC Airfoil Coordinates Database | ||
(e230-il) E230 (9.96%) | Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file | |
Eppler E230 airfoil Max thickness 10% at 29.3% chord Max camber 0% at 0% chord Max Cl/Cd 24.4 at Re# 50,000 Source UIUC Airfoil Coordinates Database | ||
(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 23.7 at Re# 50,000 Source UIUC Airfoil Coordinates Database | ||
(e230-il) E230 (9.96%) | Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file | |
Eppler E230 airfoil Max thickness 10% at 29.3% chord Max camber 0% at 0% chord Max Cl/Cd 23 at Re# 50,000 Source UIUC Airfoil Coordinates Database |
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