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Effects of forebody geometry on subsonic boundary-layer stabilityAs part of an effort to develop computational techniques for design of natural laminar flow fuselages, a computational study was made of the effect of forebody geometry on laminar boundary layer stability on axisymmetric body shapes. The effects of nose radius on the stability of the incompressible laminar boundary layer was computationally investigated using linear stability theory for body length Reynolds numbers representative of small and medium-sized airplanes. The steepness of the pressure gradient and the value of the minimum pressure (both functions of fineness ratio) govern the stability of laminar flow possible on an axisymmetric body at a given Reynolds number. It was found that to keep the laminar boundary layer stable for extended lengths, it is important to have a small nose radius. However, nose shapes with extremely small nose radii produce large pressure peaks at off-design angles of attack and can produce vortices which would adversely affect transition.
Document ID
19900016623
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Dodbele, Simha S. (Vigyan Research Associates, Inc. Hampton, VA, United States)
Date Acquired
September 6, 2013
Publication Date
August 1, 1990
Publication Information
Publisher: NASA
Subject Category
Aerodynamics
Report/Patent Number
NASA-CR-4314
NAS 1.26:4314
Meeting Information
Meeting: International Conference on Numerical Methods in Laminar and Turbulent Flow
Location: Montreal, Quebec
Country: Canada
Start Date: July 6, 1987
End Date: July 10, 1987
Accession Number
90N25939
Funding Number(s)
PROJECT: RTOP 505-61-41-02
CONTRACT_GRANT: NAS1-17919
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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