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Experimental study of the effects of Reynolds number on high angle of attack aerodynamic characteristics of forebodies during rotary motionThe National Aeronautics and Space Administration and the Defense Research Agency (United Kingdom) have ongoing experimental research programs in rotary-flow aerodynamics. A cooperative effort between the two agencies is currently underway to collect an extensive database for the development of high angle of attack computational methods to predict the effects of Reynolds number on the forebody flowfield at dynamic conditions, as well as to study the use of low Reynolds number data for the evaluation of high Reynolds number characteristics. Rotary balance experiments, including force and moment and surface pressure measurements, were conducted on circular and rectangular aftbodies with hemispherical and ogive noses at the Bedford and Farnborough wind tunnel facilities in the United Kingdom. The bodies were tested at 60 and 90 deg angle of attack for a wide range of Reynolds numbers in order to observe the effects of laminar, transitional, and turbulent flow separation on the forebody characteristics when rolling about the velocity vector.
Document ID
19950018023
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Pauley, H. (Bihrle Applied Research, Inc. Hampton, VA, United States)
Ralston, J. (Bihrle Applied Research, Inc. Hampton, VA, United States)
Dickes, E. (Bihrle Applied Research, Inc. Hampton, VA, United States)
Date Acquired
September 6, 2013
Publication Date
January 1, 1995
Subject Category
Aerodynamics
Report/Patent Number
REPT-94-4
NASA-CR-195033
NAS 1.26:195033
Accession Number
95N24443
Funding Number(s)
PROJECT: RTOP 505-68-30-01
CONTRACT_GRANT: NAS1-20228
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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