Quasi-Steady Simulations for the Efficient Generation of Static Aerodynamic Coefficients at Subsonic Velocity

Abstract

A quasi-steady sweep procedure that allows determination of the static aerodynamic coefficients for a range of angles of attack in a single simulation is extended to subsonic Mach numbers. Given a steady-state solution, the procedure can be used to generate multiple numerical simulations over a select range of angles of attack for a given set of flight conditions using the time-accurate Reynolds-Averaged NavierStokes equations. Computational Fluid Dynamics simulations are completed for a canard-controlled, fin-stabilized projectile at Mach 0.65 for a moderate range of angles of attack using a quasi-steady sweep procedure. Separate steady-state solutions are also computed at various angles of attack for comparison. Comparison of the results showed that the quasi-steady sweep procedure can provide accurate static aerodynamic coefficients efficiently if convergence at each time step is ensured.

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Document Details

Document Type
Technical Report
Publication Date
Sep 01, 2016
Accession Number
AD1017208

Entities

People

  • Sidra I. Silton

Organizations

  • United States Army Research Laboratory

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Aerodynamic Characteristics
  • Boundary Layer
  • Canard Configurations
  • Central Processing Units
  • Computational Fluid Dynamics
  • Dynamics
  • Equations
  • Fluid Dynamics
  • Fluid Flow
  • Mach Number
  • Mechanical Properties
  • Mechanics
  • Military Research
  • Physics Laboratories
  • Simulations
  • Steady State
  • Three Dimensional

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Computational Fluid Dynamics (CFD)