Numerical solutions for steady and unsteady oscillatory flow about an axi-symmetric inlet /
by Richard W. Newsome, Jr.

Description

Main Author

Newsome, Richard W., 1952-

Related Names

Air Force Wright Aeronautical Laboratories
Air Force Flight Dynamics Laboratory (U.S.)

Language(s)

English

Published

Wright-Patterson Air Force Base, Ohio : Flight Dynamics Laboratory, Air Force Wright Aeronautical Laboratories, Air Force Systems Command, United States Air Force, 1983

Subjects

Navier-Stokes equations > Navier-Stokes equations / Numerical solutions.
Reynolds stress.
Unsteady flow (Fluid dynamics)
Supersonic diffusers.
Jets > Jets / Fluid dynamics.

Summary

The unsteady, compressible, Reynolds-averaged Navier-Stokes equations were solved for the flow field about an external compression axi-symmetric inlet with a length to diameter ratio, L/D = 15.88, at Mach 2.0 and a Reynolds number based on diameter, ReD = 2.36 times 10 to the 6th power, operating in the near-critical and subcritical flow regimes. The near-critical solution reached a stable steady state while the subcritical solutions attained an unstable bounded oscillatory state, characterized by large amplitude pressure oscillations and traveling shock waves. This phenomenon is a result of a shear layer instability combined with a closed-loop feedback of reflected disturbances and the naturally occurring self-sustained oscillations are commonly known as buzz. Numerical results are given in terms of Mach contours, velocity field plots, pressure-time traces at selected stations, as well as mass flux and other mass-averaged quantities along the duct length. Comparison with experiment is also given. (Author).

Note

"Final Report for Period January 1980 - November 1982,"
"April 1983."

Physical Description

xiv, 170 pages : illustrations ; 28 cm

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