Airfoil database search
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.
(s4180-il) S4180-098-84 | Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file | |
![]() | Selig S4180 low Reynolds number airfoil Max thickness 9.8% at 26.1% chord Max camber 4% at 39.4% chord Max Cl/Cd 28.3 at Re# 50,000 Source UIUC Airfoil Coordinates Database | |
(ssca07-il) SIKORSKY SSC-A07 AIRFOIL | Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file | |
![]() | Sikorsky/Flemming SSC-A07 transonic rotorcraft airfoil Max thickness 7% at 37.7% chord Max camber 0.9% at 17.2% chord Max Cl/Cd 28.3 at Re# 50,000 Source UIUC Airfoil Coordinates Database | |
(fx68h120-il) FX 68-H-120 | Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file | |
![]() | Wortmann FX 68-H-120 airfoil Max thickness 11.8% at 25% chord Max camber 2.3% at 33.9% chord Max Cl/Cd 28.3 at Re# 50,000 Source UIUC Airfoil Coordinates Database | |
(geminism-il) GEMINI (smoothed) | Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file | |
![]() | GEMINI R/C sailplane airfoil (smoothed) Max thickness 15.4% at 34.2% chord Max camber 2.2% at 37.9% chord Max Cl/Cd 28.3 at Re# 50,000 Source UIUC Airfoil Coordinates Database | |
(goe06k-il) GOE 6K AIRFOIL | Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file | |
![]() | Gottingen 6K airfoil Max thickness 7.5% at 50% chord Max camber 3.1% at 50% chord Max Cl/Cd 28.3 at Re# 50,000 Source UIUC Airfoil Coordinates Database | |
(naca23012-il) NACA 23012 12% | Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file | |
![]() | NACA 23012 airfoil Max thickness 12% at 29.8% chord Max camber 1.8% at 12.7% chord Max Cl/Cd 28.3 at Re# 50,000 Source UIUC Airfoil Coordinates Database | |
(n64215-il) NACA 64-215 AIRFOIL | Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file | |
![]() | NACA 64(2)-215 airfoil Max thickness 15% at 34.9% chord Max camber 1.1% at 50% chord Max Cl/Cd 28.3 at Re# 50,000 Source UIUC Airfoil Coordinates Database | |
(naca642215-il) NACA 64(2)-215 | Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file | |
![]() | NACA 64(2)-215 airfoil Max thickness 15% at 34.9% chord Max camber 1.1% at 50% chord Max Cl/Cd 28.3 at Re# 50,000 Source UIUC Airfoil Coordinates Database | |
(hsnlf213-il) HSNLF(1)-0213 AIRFOIL | Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file | |
![]() | NASA/Langley HSNLF(1)-0213 high speed natural laminar flow airfoil Max thickness 13.3% at 42.4% chord Max camber 1.4% at 32.4% chord Max Cl/Cd 28.3 at Re# 50,000 Source UIUC Airfoil Coordinates Database | |
(eh2012-il) EH 2.0/12 | Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file | |
![]() | John Yost EH 2.0/12 for tailless R/C aircraft Max thickness 12% at 28.7% chord Max camber 2% at 25.9% chord Max Cl/Cd 28.3 at Re# 50,000 Source UIUC Airfoil Coordinates Database |
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