Airfoil Tools
Search 1638 airfoils

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Your Reynold number range is 50,000 to 1,000,000. (set)

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.

(goe180-il) GOE 180 (MVA H.26) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 180 (MVA H.26) airfoil Max thickness 8.7% at 30% chord Max camber 4.4% at 40% chord Max Cl/Cd 59.5 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe137-il) GOE 137 (MVA H.15) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 137 (MVA H.15) airfoil Max thickness 8.6% at 29.9% chord Max camber 4.4% at 39.9% chord Max Cl/Cd 59.5 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe332-il) GOE 332 (PFALZ 61) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 332 (Pfalz 61) airfoil Max thickness 11.8% at 29.8% chord Max camber 6.4% at 39.8% chord Max Cl/Cd 59.4 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(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
	LWK 80-100 symmetrical airfoil Max thickness 10.1% at 40.2% chord Max camber 0% at 0% chord Max Cl/Cd 59.4 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(fx601261-il) WORTMANN FX 60-126/1 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 60-126/1 airfoil Max thickness 12.6% at 27.9% chord Max camber 4% at 56.5% chord Max Cl/Cd 59.4 at Re# 100,000 Source UIUC Airfoil Coordinates Database

(sd6080-il) SD6080 (9.2%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig/Donovan SD6080 low Reynolds number airfoil Max thickness 9.2% at 30.9% chord Max camber 3.2% at 44.7% chord Max Cl/Cd 59.4 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe399-il) GOE 399 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 399 airfoil Max thickness 6.9% at 29.9% chord Max camber 4.2% at 39.9% chord Max Cl/Cd 59.4 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe546-il) GOE 546 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 546 airfoil Max thickness 10.4% at 30% chord Max camber 3.6% at 50% chord Max Cl/Cd 59.4 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe79-il) GOE 79 (PFALZ 11) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 79 (Pfalz 11) airfoil Max thickness 6.2% at 14.9% chord Max camber 6% at 29.9% chord Max Cl/Cd 59.4 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(hs1404-il) HAM-STD HS1-404 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	HS1 family of prop airfoils from US Patent No. 4 Max thickness 4% at 18% chord Max camber 3.1% at 46% chord Max Cl/Cd 59.4 at Re# 100,000 Source UIUC Airfoil Coordinates Database