Algorithm and code development for unsteady threedimensional NavierStokes equations
Abstract
Aeroelastic tests require extensive cost and risk. An aeroelastic windtunnel experiment is an order of magnitude more expensive than a parallel experiment involving only aerodynamics. By complementing the windtunnel experiments with numerical simulations, the overall cost of the development of aircraft can be considerably reduced. In order to accurately compute aeroelastic phenomenon it is necessary to solve the unsteady Euler/NavierStokes equations simultaneously with the structural equations of motion. These equations accurately describe the flow phenomena for aeroelastic applications. At ARC a code, ENSAERO, is being developed for computing the unsteady aerodynamics and aeroelasticity of aircraft, and it solves the Euler/NavierStokes equations. The purpose of this cooperative agreement was to enhance ENSAERO in both algorithm and geometric capabilities. During the last five years, the algorithms of the code have been enhanced extensively by using highresolution upwind algorithms and efficient implicit solvers. The zonal capability of the code has been extended from a onetoone grid interface to a mismatching unsteady zonal interface. The geometric capability of the code has been extended from a single oscillating wing case to a fullspan wingbody configuration with oscillating control surfaces. Each time a new capability was added, a proper validation case was simulated, and the capability of the code was demonstrated.
 Publication:

Unknown
 Pub Date:
 April 1994
 Bibcode:
 1994acdu.rept.....O
 Keywords:

 Aerodynamic Characteristics;
 Aerodynamics;
 Aeroelasticity;
 Algorithms;
 NavierStokes Equation;
 Unsteady Aerodynamics;
 Wind Tunnel Tests;
 BodyWing Configurations;
 Control Surfaces;
 Equations Of Motion;
 Oscillating Flow;
 Oscillations;
 Fluid Mechanics and Heat Transfer