Numerical computation of subsonic conical diffuser flows with nonuniform turbulent inlet conditions /
J.C. Chien.

Description

Main Author

Chien, J. C.

Related Names

United States. Air Force.
Arnold Engineering Development Center
ARO, Inc.

Language(s)

English

Published

Arnold Air Force Base, Tennessee : Arnold Engineering Development Center, Engine Test Facility, Air Force Systems Command, United States Air Force, 1977.

Subjects

Airplanes > Airplanes / Turbojet engines > Airplanes / Turbojet engines / Air intakes.
Boundary layer noise.
Diffusers > Diffusers / Fluid dynamics.

Summary

Numerical solutions of the Navier-Stokes equations are obtained and results presented for conical diffuser flows with turbulent nonuniform inlet conditions. The turbulent flow field is described by a two-equation, low-Reynolds-number k-epsilon model with a new turbulence model for axisymmetric flow. Fast convergence is achieved with an improved initial flow-field guess and a multiple grid Gauss-Seidel iteraction method. Comparisons are made with existing data for several diffuser divergence angles with and without flow separation. Good agreement was obtained between theory and experiment. (Author).

Note

"September 1977."
"Final Report: October 1976 -- May 1977."

Physical Description

73 pages : illustrations ; 28 cm

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