Accession Number : ADA325743

Title :   Unstructured h-p Finite Elements for Unsteady High Speed Flows.

Descriptive Note : Final rept. 1 Apr 95-30 Nov 96,

Corporate Author : BROWN UNIV PROVIDENCE RI DIV OF APPLIED MATHEMATICS

Personal Author(s) : Karniadakis, George E.

PDF Url : ADA325743

Report Date : APR 1997

Pagination or Media Count : 6

Abstract : There is currently a great interest in predicting the motion and corresponding loads of highly maneuverable aircraft capable of controlled flight at very high angles of attack. The design of air-to-air missiles could also benefit greatly from a better understanding of high angle of attack supersonic flight. Unsteady separation and formation of strongly asymmetric vortices from such bodies can introduce substantial lateral forces and yawing moments that must be counteracted or possibly used intelligently to aid in controlling the flight of the body. The majority of recent numerical studies has focused on steady and relatively low Mach number flows. Special algorithms have been developed for the design of high quality meshes to ensure convergence of the numerical solution in these complex configurations. The objective of this project is to develop hybrid DNS-LES numerical capabilities to predict forces and details of flow structure for unsteady viscous flows around complex geometry three dimensional aerodynamic configurations at high speed.

Descriptors :   *AERODYNAMIC CONFIGURATIONS, *UNSTEADY FLOW, *AIR TO AIR MISSILES, *VISCOUS FLOW, MANEUVERABILITY, YAW, FLIGHT CONTROL SYSTEMS, ATTACK, NUMERICAL ANALYSIS, VORTICES, COMPUTATIONAL FLUID DYNAMICS, MESH, ASYMMETRY, CONVERGENCE, SUPERSONIC FLIGHT, MACH NUMBER, SUPERSONIC FLOW, EXPONENTIAL FUNCTIONS, NAVIER STOKES EQUATIONS, HIGH ANGLES, GALERKIN METHOD.

Subject Categories : Aerodynamics
      Fluid Mechanics
      Guided Missiles

Distribution Statement : APPROVED FOR PUBLIC RELEASE