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DTIC ADA1012103: High Angle of Attack Missile Aerodynamics at Mach ...
by Defense Technical Information Center
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A large body of wind tunnel data was generated by tests
of a smooth missile model with several interchangeable
nose parts. The tests were conducted at subsonic through
supersonic speeds at angles of attack from 0 to 180
degrees. They were part of the FDL and SAMSO technology
studies which preceded design of the MX missile.
Measurements of both surface pressures and total forces
and moments were made at a variety of Mach numbers and
Reynolds number combinations. This data was supplemented
with wake flow-field measurements of the impact pressure
and flow direction at angles of attack where maximum
induced side force was expected to occur. A review of the
literature for subsonic and transonic aerodynamic
characteristics of bodies of revolution was conducted. A
comprehensive discussion is provided of the important
variables of the high angle of attack flow phenomena. The
test data provided insight into the effect of several
variables that had not been adequately treated in the
past. The high angle of attack data was analyzed to
deduce the vortex shedding location, the vortex strength,
and the vortex paths in the wake. Discrete vortex theory
was examined as a method which could be modified, based
on experimental data, and used to predict the aerodynamic
characteristics of missiles to greater accuracy. An
alternate approach to developing a prediction method was
explored by means of a correlation of the surface
pressure data.
Date Published: 2020-01-07 10:13:18
Identifier: DTIC_ADA1012103
Item Size: 94307345
Language: english
Media Type: texts
# Topics
DTIC Archive; Dahlem, Valentine; AIR ...
# Collections
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