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.

(goe499-il) GOE 499 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 499 airfoil Max thickness 6.8% at 30% chord Max camber 5.9% at 50% chord Max Cl/Cd 99.1 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(lrn1007-il) lrn1007		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	LRN(1)-1007 low Reynolds number airfoil Max thickness 7.3% at 39.8% chord Max camber 5.9% at 44.6% chord Max Cl/Cd 98.7 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(s1223rtl-il) S1223 RTL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Richard T. LaSalle modification of the S1223 to S1223RTL Max thickness 13.5% at 19.9% chord Max camber 8.3% at 55.2% chord Max Cl/Cd 98 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(sg6043-il) SG6043		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig / Giguere SG6043 wind turbine airfoil (high L/D) Max thickness 10% at 32.1% chord Max camber 5.1% at 53.3% chord Max Cl/Cd 98 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(ah79100c-il) AH 79-100 C AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Althaus AH 79-100C airfoil Max thickness 9.9% at 30.9% chord Max camber 6.7% at 50% chord Max Cl/Cd 97.6 at Re# 200,000 Source UIUC Airfoil Coordinates Database

(hs1708-il) HAM-STD HS1-708 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 7.9% at 22% chord Max camber 5% at 46% chord Max Cl/Cd 97.3 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe494-il) GOE 494 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 494 airfoil Max thickness 5% at 20% chord Max camber 5.1% at 50% chord Max Cl/Cd 97 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(ah79100c-il) AH 79-100 C AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Althaus AH 79-100C airfoil Max thickness 9.9% at 30.9% chord Max camber 6.7% at 50% chord Max Cl/Cd 97 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(e385-il) E385 (8.41%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E385 airfoil Max thickness 8.4% at 29.6% chord Max camber 5.3% at 47.5% chord Max Cl/Cd 96.8 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(e385-il) E385 (8.41%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E385 airfoil Max thickness 8.4% at 29.6% chord Max camber 5.3% at 47.5% chord Max Cl/Cd 96.8 at Re# 200,000 Source UIUC Airfoil Coordinates Database