NDLI: On the design of airfoils in which the transition of the boundary layer is delayed

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On the design of airfoils in which the transition of the boundary layer is delayed

Content Provider	NASA Technical Reports Server (NTRS)
Copyright Year	1952
Description	A method is presented for designing suitable thickness distributions and mean camber lines for airfoils permitting extensive chordwise laminar flow. Wind tunnel and flight tests confirming the existence of laminar flow; possible maintenance of laminar flow by area suction; and the effects of wind tunnel turbulence and surface roughness on the promotion of premature boundary layer transition are discussed. In addition, estimates of profile drag and scale effect on maximum lift of the derived airfoils are made.
File Size	3210328
Page Count	75
File Format	PDF
Alternate Webpage(s)	http://archive.org/details/NASA_NTRS_Archive_19930093879
Archival Resource Key	ark:/13960/t5x67v17f
Language	English
Publisher Date	1952-10-01
Access Restriction	Open
Subject Keyword	Boundary Layer Control - Airfoils Pressure Distribution - Airfoils - Naca 0010 Wing Section Theory Airfoils - Thickness Pressure Distribution - Airfoils - Lb 24 Airfoils, Symmetrical Flow, Laminar Boundary Layer Transition - Airfoils Airfoils, Cambered Pressure Distribution - Airfoils - Naca 23012 Wing Sections - Section Variables Boundary Layer Characteristics - Wing Sections Reynolds Number Effects - Wing Sections Flow, Turbulent Airfoils, Laminar-flow Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science
Content Type	Text
Resource Type	Technical Report

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