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.
(bqm34-il) RYAN BQM-34 FIREBEE WING AIRFOIL | Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file | |
Ryan BQM-34 Firebee wing airfoil (NACA 63-014A W/NACA 0014 nose and thinned to .09899 to account for sweep) Max thickness 9.9% at 32.5% chord Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database | ||
(raf27-il) RAF 27 AIRFOIL | Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file | |
RAF-27 airfoil Max thickness 9.8% at 30% chord Max camber 0% at 0% chord 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 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 Source NASA | ||
(s9026-il) S9026 (9.5%) | Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file | |
Selig S9026 (9.5%) symmetrical horizontal stab airfoil used on the Opus R/C sailplane Max thickness 9.5% at 27.3% chord Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database | ||
(n0009sm-il) NACA-0009 9.0% smoothed | Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file | |
NACA 0009 airfoil (smoothed) Max thickness 9% at 30.9% chord Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database | ||
(s9032-il) S9032 (9%) | Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file | |
Selig S9032 (9%) symmetrical horizontal stab airfoil used on the Blackhawk R/C sailplane Max thickness 9% at 25% chord Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database | ||
(ys900-il) YS-900 | Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file | |
YS900 hyrdofoil (Shen / Eppler) Max thickness 9% at 52.5% chord Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database | ||
(eh0009-il) EH 0.0/9.0 | Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file | |
John Yost EH 0.0/9.0 for tailless R/C aircraft Max thickness 9% at 28.7% chord Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database | ||
(ea61009-il) EPPLER EA 6(-1)-009 AIRFOIL | Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file | |
Eppler EA 6(-1)-009 airfoil Max thickness 9% at 30% chord Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database |
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