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Bumblebee program, aerodynamic data. Part 2: Flow fields at Mach number 2.0Available flow field data which can be used in validating theoretical procedures for computing flow fields around supersonic missiles are presented. Tabulated test data are given which define the flow field around a conical-nosed cylindrical body in a crossflow plane corresponding to a likely tail location. The data were obtained at a Mach number of 2.0 for an angle of attack of 0 to 23 degrees. The data define the flow field for cases both with and without a forward wing present.
Document ID
19790013873
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Barnes, G. A. (Johns Hopkins Univ. Silver Spring, MD, United States)
Cronvich, L. L. (Johns Hopkins Univ. Silver Spring, MD, United States)
Date Acquired
September 3, 2013
Publication Date
April 1, 1979
Subject Category
Aerodynamics
Report/Patent Number
NASA-CR-3115
Accession Number
79N22044
Funding Number(s)
CONTRACT_GRANT: NASA ORDER L-60036-A
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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