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Wind tunnel pressure study and Euler code validation of a missile configuration with 77 deg swept delta wings at supersonic speedsA wind-tunnel pressure study was conducted on an axisymmetric missile configuration in the Unitary Plan Wind Tunnel at NASA Langley Research Center. The Mach numbers ranged from 1.70 to 2.86 and the angles of attack ranged from minus 4 degrees to plus 24 degrees. The computational accuracy for limited conditions of a space-marching Euler code was assessed.
Document ID
19890009044
Acquisition Source
Legacy CDMS
Document Type
Thesis/Dissertation
Authors
Fulton, Patsy S. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 5, 2013
Publication Date
November 1, 1988
Subject Category
Aerodynamics
Report/Patent Number
NAS 1.15:101531
NASA-TM-101531
Accession Number
89N18415
Funding Number(s)
PROJECT: RTOP 505-61-71-01
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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