Airfoil Tools
Search 1638 airfoils

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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.

(hh02-il) HUGHES HELICOPTERS HH-02 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Hughes helicopters HH-02 rotorcraft airfoil Max thickness 9.6% at 30% chord Max camber 2% at 40% chord Source UIUC Airfoil Coordinates Database
(isa962-il) I.S.A. 962		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	I.S.A. 962 airfoil Max thickness 9.6% at 20% chord Max camber 4.6% at 40% chord Source UIUC Airfoil Coordinates Database
(mh44-il) MH 44 9.66%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 44 for flying wings Max thickness 9.6% at 27.1% chord Max camber 1.5% at 36.9% 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
(s4061-il) S4061-096-84		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S4061 low Reynolds number airfoil Max thickness 9.6% at 30.9% chord Max camber 3.3% at 44.7% chord Source UIUC Airfoil Coordinates Database

(sd7084-il) SD7084 (9.6%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig/Donovan SD7084 low Reynolds number airfoil Max thickness 9.6% at 29.5% chord Max camber 2.3% at 38.9% chord Source UIUC Airfoil Coordinates Database
(goe134-il) GOE 134 (MVA H.12) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 134 (MVA H.12) airfoil Max thickness 9.5% at 30% chord Max camber 4% at 30% chord Source UIUC Airfoil Coordinates Database
(goe182-il) GOE 182 (MVA H.27) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 182 (MVA H.27) airfoil Max thickness 9.5% at 19.9% chord Max camber 5.3% at 39.9% chord Source UIUC Airfoil Coordinates Database
(goe407-il) GOE 407 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 407 airfoil Max thickness 9.5% at 29.9% chord Max camber 4.8% at 39.9% chord Source UIUC Airfoil Coordinates Database
(hq2195-il) HQ 2.1/9.5 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Quabeck HQ 2.1/9.5 R/C sailplane airfoil Max thickness 9.5% at 35% chord Max camber 2.1% at 55% chord Source UIUC Airfoil Coordinates Database