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.

(rc12b3-il) NASA/LANGLEY RC-12(B)3 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA/Langley RC-12(B)3 rotorcraft airfoil Max thickness 12% at 38% chord Max camber 2.2% at 34.3% chord Max Cl/Cd 76.4 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(c141c-il) LOCKHEED C-141 BL426.57 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Lockheed-Georgia C-141 transonic wing airfoils Max thickness 11% at 40.2% chord Max camber 1.3% at 50% chord Max Cl/Cd 76.4 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(sc20414-il) NASA SC(2)-0414 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA SC(2)-0414 airfoil (NASA TP-2969) Max thickness 14% at 36% chord Max camber 1.5% at 83% chord Max Cl/Cd 76.3 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(giiib-il) GIII BL45 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Grumman/Gulfstream GIII transonic airfoils Max thickness 10.4% at 39.7% chord Max camber 0.8% at 24.7% chord Max Cl/Cd 76.3 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(naca66206-il) NACA 66-206		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 66-206 airfoil Max thickness 6% at 45% chord Max camber 1.1% at 50% chord Max Cl/Cd 76.3 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database

(goe548-il) GOE 548 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 548 airfoil Max thickness 11.9% at 40% chord Max camber 2.3% at 50% chord Max Cl/Cd 76.3 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(nlf0115-il) NLF(1)-0115		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA/Langley/Somers-Selig-Maughmer NLF(1)-0115 natural laminar flow airfoil Max thickness 15% at 44.1% chord Max camber 1.8% at 30% chord Max Cl/Cd 76.3 at Re# 1,000,000 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 Max Cl/Cd 76.3 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(naca662215-il) NACA 66(2)-215		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 66(2)-215 airfoil Max thickness 15% at 45% chord Max camber 1.1% at 50% chord Max Cl/Cd 76.2 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(npl9626-il) NPL 9626 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NPL 9626 rotorcraft airfoil Max thickness 12.1% at 30.9% chord Max camber 0.7% at 30.9% chord Max Cl/Cd 76.1 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database