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A study of the vortex flow over 76/40-deg double-delta wingA low-speed wind-tunnel study of the flow about a 76/40-deg double-delta wing is described for angles of attack ranging from -10 to 25 deg and Reynolds numbers ranging from 0.5 to 1.5 Million. The study was conducted to provide data for the purpose of understanding the vortical flow behavior and for validating Computational Fluid Dynamics methods. Flow visualization tests have provided insight into the effect of the angle of attack and Reynolds number of the vortex-dominated flow both on and off of the surface of the double-delta wing. Upper surface pressure recordings from pressure orifices and Pressure Sensitive Paint have provided data on the pressures induced by the vortices. Flowfield surveys were carried out at an angle of attack of 10 deg by using a thin 5-hole probe. Numerical solutions of the compressible thin-layer Navier-Stokes equations were conducted and compared to the experimental data.
Document ID
19950017046
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Verhaagen, N. G. (Technische Hogeschool Delft, Netherlands)
Jenkins, L. N. (NASA Langley Research Center Hampton, VA., United States)
Kern, S. B. (Naval Air Warfare Center Warminster, PA., United States)
Washburn, A. E. (Vigyan Research Associates, Inc. Hampton, VA., United States)
Date Acquired
September 6, 2013
Publication Date
February 1, 1995
Publication Information
Publisher: NASA
Subject Category
Fluid Mechanics And Heat Transfer
Report/Patent Number
NASA-CR-195032
AIAA PAPER 95-0560
ICASE-95-5
NAS 1.26:195032
Accession Number
95N23466
Funding Number(s)
PROJECT: RTOP 505-90-52-01
CONTRACT_GRANT: NAS1-19480
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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