Accession Number : ADA304583
Title : A Study of Asymmetric Vortex Shedding Behind Missiles at High Angle of Attack Using Dynamic Solution Adaptive Meshes.
Descriptive Note : Final technical rept. Jun 92-Aug 95,
Corporate Author : CINCINNATI UNIV OH DEPT OF AEROSPACE ENGINEERING AND ENGINEERING MECHANICS
Personal Author(s) : Orkwis, Paul D.
PDF Url : ADA304583
Report Date : 09 OCT 1995
Pagination or Media Count : 8
Abstract : Vortices about the leeward side of cones at incidence become asymmetric past a critical incidence ratio. They consequently produce large side forces that lead to in flight control and maneuverability problems. The origins of this asymmetry have yet to be fully understood. Questions exist as to the nature of the asymmetry instability, the bifurcation process that occurs as the solution transitions from symmetric to asymmetric, and the numerical requirements for its computation. The reported research was initiated to seek answers to these questions.
Descriptors : *VORTEX SHEDDING, *CONICAL BODIES, RATIOS, MANEUVERABILITY, FLIGHT CONTROL SYSTEMS, NUMERICAL ANALYSIS, COMPUTATIONAL FLUID DYNAMICS, ANGLE OF ATTACK, MESH, ASYMMETRY, AERODYNAMIC LOADING, INFLIGHT, BOUNDARY LAYER TRANSITION, NAVIER STOKES EQUATIONS, DOWNSTREAM FLOW, HIGH ANGLES.
Subject Categories : Fluid Mechanics
Distribution Statement : APPROVED FOR PUBLIC RELEASE