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.

(hs1430-il) HAM-STD HS1-430 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 30% at 34% chord Max camber 3% at 44% chord Source UIUC Airfoil Coordinates Database
(hs1606-il) HAM-STD HS1-606 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 6% at 18% chord Max camber 4.4% at 46% chord Source UIUC Airfoil Coordinates Database
(hs1620-il) HAM-STD HS1-620 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 20% at 34% chord Max camber 4.1% at 44% chord 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 Source UIUC Airfoil Coordinates Database
(hs1712-il) HAM-STD HS1-712 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 12% at 36% chord Max camber 4.9% at 44% chord 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 Source UIUC Airfoil Coordinates Database
(ht05-il) HT05		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Drela HT05 airfoil Max thickness 4.8% at 17.1% chord Max camber 0% at 63.3% chord Source UIUC Airfoil Coordinates Database
(ht08-il) HT08		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Drela HT08 airfoil Max thickness 5% at 20.2% chord Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database
(ht12-il) HT12		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Drela HT12 airfoil Max thickness 5% at 18.6% chord Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database
(ht22-il) HT22		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Drela HT22 airfoil Max thickness 5.1% at 19.1% chord Max camber 1.1% at 22.7% chord Source UIUC Airfoil Coordinates Database

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