Flowfield measurements in the wake of a missile at high angle of attack
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Authors
Johnson, Dan A.
Subjects
Vertical launch
Surface-to-air missile
High angle of attack aerodynamics
Turbulence
Body of revolution
Vortex asymmetry
Surface-to-air missile
High angle of attack aerodynamics
Turbulence
Body of revolution
Vortex asymmetry
Advisors
Howard, Richard M.
Date of Issue
1989-09
Date
September 1989
Publisher
Monterey, California. Naval Postgraduate School
Language
en_US
Abstract
The flowfield about a vertically-launched surface-to-air missile model at an angle of attack of 50 degrees and a Reynolds number of 1.1x10(5) was investigated in a low-speed wind tunnel at the Naval Postgraduate School. Determined were the location and intensity of the asymmetric vortices in the wake of the model using planar velocity vector, total pressure coefficient, and vorticity plots. Two model configurations were tested: one at a roll angle of 0 degrees (the "+" configuration) and the other at a roll angle of 45 degrees (the "x" configuration). Two flowfield conditions were used: one with no turbulence and the other with turbulence of a length scale on the order of the size of the nose-generated vortices. The following conclusions were reached: 1) the
addition of turbulence changed the magnitudes of the variables without changing the patterns in the plots; 2) changing roll angle significantly altered the patterns of the plots; 3) in general, the locations of the vortices as indicated by the velocity plots do not coincide with the centers for the pressure or vorticity plots; 4) total pressure losses coincide with changes in magnitude of side force as noted in an earlier study.
Type
Thesis
Description
Series/Report No
Department
Aeronautics and Astronautics
Organization
Naval Postgraduate School (U.S.)
Identifiers
NPS Report Number
Sponsors
Funder
Format
64 p.
Citation
Distribution Statement
Approved for public release; distribution is unlimited.
Rights
This publication is a work of the U.S. Government as defined in Title 17, United States Code, Section 101. Copyright protection is not available for this work in the United States.