Numerical Simulation of Unsteady Flow in a Compressor Rotor Cascade.

Abstract

Unsteady flow in a two-dimensional compressor rotor is computed by solving the time-dependent compressible Navier-Stokes equations for flow between two adjacent rotor blades. The computations are carried out on a CDC Cyber 845 computer and a CRAY XMP computer using MacCormack's explicit finite difference scheme. The primary objective of this program is to numerically simulate the rotor flow accounting for the effects of wakes from the upstream stator and inlet guide vane. Particular attention is focused on the influence of unsteady effects on the mass flow rate, shock structure, and shock wave-boundary layer interaction. Keywords: Compressor rotor, Navier Stokes equations, Numerical simulation, Unsteady flow.

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Document Details

Document Type
Technical Report
Publication Date
Nov 01, 1986
Accession Number
ADA188284

Entities

People

  • James N. Scott

Organizations

  • University of Dayton

Tags

Communities of Interest

  • Air Platforms
  • Cyber

DTIC Thesaurus Topics

  • Air Force
  • Air Force Facilities
  • Boundary Layer
  • Classification
  • Compressor Rotors
  • Computational Fluid Dynamics
  • Equations
  • Fluid Dynamics
  • Fluid Flow
  • Mach Number
  • Physics Laboratories
  • Pressure Distribution
  • Stagnation Pressure
  • Static Pressure
  • Steady Flow
  • Steady State
  • Viscous Flow

Fields of Study

  • Physics

Readers

  • Aerodynamics.
  • Finite Element Method (FEM) for solving Partial Differential Equations (PDEs)
  • Fluid Mechanics and Fluid Dynamics.

Technology Areas

  • Cyber
  • Cyber - Cryptography