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Natural laminar flow and airplane stability and controlLocation and mode of transition from laminar to turbulent boundary layer flow have a dominant effect on the aerodynamic characteristics of an airfoil section. The influences of these parameters on the sectional lift and drag characteristics of three airfoils are examined. Both analytical and experimental results demonstrate that when the boundary layer transitions near the leading edge as a result of surface roughness, extensive trailing-edge separation of the turbulent boundary layer may occur. If the airfoil has a relatively sharp leading-edge, leading-edge stall due to laminar separation can occur after the leading-edge suction peak is formed. These two-dimensional results are used to examine the effects of boundary layer transition behavior on airplane longitudinal and lateral-directional stability and control.
Document ID
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Vandam, Cornelis P.
(Vigyan Research Associates, Inc. Hampton, VA, United States)
Date Acquired
September 5, 2013
Publication Date
May 1, 1986
Publication Information
Publication: NASA, Langley Research Center, Laminar Flow Aircraft Certification
Subject Category
Aircraft Stability And Control
Accession Number
Funding Number(s)
Distribution Limits
Work of the US Gov. Public Use Permitted.
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